Airworthiness Directives; Dornier Model 328-300 Series Airplanes

[Federal Register Volume 67, Number 3 (Friday, January 4, 2002)]
[Rules and Regulations]
[Pages 509-510]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-147]



[[Page 509]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-174-AD; Amendment 39-12584; AD 2001-26-18]
RIN 2120-AA64


Airworthiness Directives; Dornier Model 328-300 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 certain Dornier Model 328-300 series airplanes, that 
requires, for certain airplanes, a one-time torque test (inspection) of 
the attachment bolts of the forward engine mount vibration isolators to 
determine if the bolts are adequately torqued, and corrective action, 
if necessary. For all airplanes, this amendment prohibits installation 
of an attachment bolt on the forward engine mount vibration isolators, 
unless the attachment bolt is torqued within certain limits. These 
actions are necessary to prevent failure of the engine mount, which 
could result in separation of the engine from the airplane. This action 
is intended to address the identified unsafe condition.

DATES: Effective February 8, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 8, 2002.

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; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom Groves, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1503; 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 certain Dornier Model 328-300 
series airplanes was published in the Federal Register on September 14, 
2001 (66 FR 47901). That action proposed to require, for certain 
airplanes, a one-time torque test (inspection) of the attachment bolts 
of the forward engine mount vibration isolators to determine if the 
bolts are adequately torqued, and corrective action, if necessary. For 
all airplanes, that action also proposed to prohibit installation of an 
attachment bolt on the forward engine mount vibration isolators, unless 
the attachment bolt is torqued within certain limits.

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 36 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 work hours 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 AD on U.S. operators is estimated to be $4,320, or $120 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

    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:

2001-26-18  Dornier Luftfahrt GMBH: Amendment 39-12584. Docket 2001-
NM-174-AD.

    Applicability: Model 328-300 series airplanes, on which a 
forward engine mount vibration isolator has been removed or 
reinstalled since the date of manufacture of the airplane, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 prevent failure of the engine mount, which could result in 
separation of the engine from the airplane, accomplish the 
following:

[[Page 510]]

One-Time Inspection

    (a) For airplanes on which a forward engine mount vibration 
isolator has been removed or reinstalled prior to the effective date 
of this AD: Within 2,500 flight cycles after the first removal or 
reinstallation of a forward engine mount vibration isolator, or 
within 30 days after the effective date of this AD, whichever comes 
later, do a one-time torque test (inspection) of the attachment 
bolts of the forward engine mount vibration isolators on the left- 
and right-hand sides of the airplane to determine if the bolts are 
adequately torqued, according to Dornier Service Bulletin SB-328J-
71-109, dated March 26, 2001, including Dornier 328JET Aircraft 
Maintenance Manual (AMM) Temporary Revision (TR) 71-130, dated March 
8, 2001.

Replacement of Bolts

    (b) During the inspection required by paragraph (a) of this AD, 
if the torque value of any attachment bolt is found to be outside 
the limits specified in Dornier Service Bulletin SB-328J-71-109, 
dated March 26, 2001, including Dornier 328JET AMM TR 71-130, dated 
March 8, 2001: Before further flight, do all actions associated with 
replacing all bolts on the vibration isolator on which the 
improperly torqued bolt was found (including performing a detailed 
visual inspection to determine the condition of components of the 
vibration isolator and replacement of any damaged components with 
new components, removing the existing bolts and washers that attach 
the forward engine mount vibration isolators to the engine, 
installing new bolts to reattach the forward engine mount vibration 
isolators to the engine, and torquing the new bolts to adequate 
torque values), according to the service bulletin.

    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.''

Torque Requirements

    (c) For all airplanes: As of the effective date of this AD, no 
one may install an attachment bolt on the forward engine mount 
vibration isolators on any airplane, unless the attachment bolt is 
torqued within the limits specified in Dornier 328JET AMM TR 71-130, 
dated March 8, 2001.

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, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. 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

    (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) The actions shall be done in accordance with Dornier Service 
Bulletin SB-328J-71-109, dated March 26, 2001, including Dornier 
328JET Aircraft Maintenance Manual Temporary Revision 71-130, dated 
March 8, 2001. 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 FAIRCHILD DORNIER, 
DORNIER Luftfahrt 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 Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

    Note 4: The subject of this AD is addressed in German 
airworthiness directive 2001-163, dated June 14, 2001.

Effective Date

    (g) This amendment becomes effective on February 8, 2002.

    Issued in Renton, Washington, on December 21, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-147 Filed 1-3-02; 8:45 am]
BILLING CODE 4910-13-U

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