[Federal Register Volume 63, Number 225 (Monday, November 23, 1998)]
[Rules and Regulations]
[Pages 64608-64609]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31009]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-137-AD; Amendment 39-10892; AD 98-24-06]
RIN 2120-AA64
Airworthiness Directives; Dornier-Werke G.m.b.H. Model Do 27 Q-6
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all Dornier-Werke G.m.b.H. (Dornier) Model Do 27 Q-6
airplanes. This AD requires repetitively inspecting the rivets that
attach the forward stabilizer attach fitting to the airplane fuselage
for looseness, and replacing any loose rivets. This AD is the result of
mandatory continuing airworthiness information (MCAI) issued by the
airworthiness authority for Germany. The actions specified by this AD
are intended to prevent the stabilizer from detaching at the forward
stabilizer attach flanges because of loose rivets, which could result
in reduced or loss of control of the airplane.
DATES: Effective December 28, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 28, 1998.
ADDRESSES: Service information that applies to this AD may be obtained
from Daimler-Benz Aerospace, Dornier, Product Support, P.O. Box 1103,
D-82230 Wessling, Federal Republic of Germany; telephone: (08153) 300;
facsimile: (08153) 302985. This information may also be examined at the
Federal Aviation Administration (FAA), Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 97-CE-137-AD, Room 1558,
601 E. 12th Street, Kansas City, Missouri 64106; or at the Office of
the Federal Register, 800 North Capitol Street, NW, suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate, 1201 Walnut, suite 900,
Kansas City, Missouri 64106; telephone: (816) 426-6934; facsimile:
(816) 426-2169.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to all Dornier Model Do
27 Q-6 airplanes was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on September 14, 1998 (63 FR 49048). The
NPRM proposed to require repetitively inspecting the rivets that attach
the forward stabilizer attach fitting to the airplane fuselage for
looseness, and replacing any loose rivets. Accomplishment of the
proposed action as specified in the NPRM would be required in
accordance with Dornier Service Bulletin No. 1140-0000, Date of Issue:
September 29, 1995.
The NPRM was the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for Germany.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Compliance Time of This AD
The initial compliance time of this AD is presented in calendar
time in order to assure that any rivets that are already loose are
detected and corrected in a timely manner. The FAA has determined that
3 calendar months is a reasonable time for all owners/operators of the
affected airplanes to comply with the initial inspection and possible
replacement specified in this AD.
The repetitive inspection interval is at 100 hours time-in-service
(TIS). After examining the information related to this subject, the FAA
has determined that the rivets should not become loose within 100 hours
TIS if they were not found loose or replaced during the last
inspection. This will not put an undue burden on low usage airplanes of
having to repetitively inspect every 3 calendar months if the airplanes
had been rarely or never utilized.
Cost Impact
The FAA estimates that 13 airplanes in the U.S. registry will be
affected by the initial inspection, that it will take approximately 1
workhour per airplane to accomplish the inspection, and that the
average labor rate is approximately $60 an hour. Based on these
figures, the total cost impact of the initial inspection on U.S.
operators is estimated to be $780, or $60 per airplane. These figures
only take into account the costs of the initial inspection and do not
take into account the costs of any repetitive inspections. The FAA has
no way of determining the number of repetitive inspections each owner/
operator will incur over the life of the affected airplanes.
If loose rivets are found and replacement is necessary, the FAA
estimates that it will take approximately 8 workhours per airplane to
accomplish the replacement, and that the average labor rate is
approximately $60 an hour. Replacement rivets will be supplied by
Dornier at no cost to the owners/operators of the affected airplanes.
Based on these figures, the cost impact of the replacement on U.S.
operators is estimated to be $480 per airplane where loose rivets are
found.
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
[[Page 64609]]
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 copy of the final evaluation prepared for this
action is contained in the Rules Docket. A copy of it may be obtained
by contacting 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 a new airworthiness directive
(AD) to read as follows:
98-24-06 Dornier-Werke G.M.B.H.: Amendment 39-10892; Docket No. 97-
CE-137-AD.
Applicability: Model Do 27 Q-6 airplanes, all serial numbers,
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 in the body of this AD, unless
already accomplished.
To prevent the stabilizer from detaching at the forward
stabilizer attach flanges because of loose rivets, which could
result in reduced or loss of control of the airplane, accomplish the
following:
(a) Within the next 3 calendar months after the effective date
of this AD, and thereafter at intervals not to exceed 100 hours
time-in-service (TIS), inspect the rivets that attach the forward
stabilizer attach fitting to the airplane fuselage for looseness.
Accomplish these inspections in accordance with the PROCEDURE
section of Dornier Service Bulletin (SB) No. 1140-0000, Date of
Issue: September 29, 1995.
(b) If loose rivets are found during any inspection required in
paragraph (a) of this AD, prior to further flight, replace any loose
rivets in accordance with the PROCEDURE section of Dornier SB No.
1140-0000, Date of Issue: September 29, 1995.
(c) 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.
(d) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Small Airplane
Directorate, 1201 Walnut, suite 900, Kansas City, Missouri 64106.
The request shall be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Small Airplane Directorate.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(e) Questions or technical information related to Dornier
Service Bulletin No. 1140-0000, Date of Issue: September 29, 1995,
should be directed to Daimler-Benz Aerospace, Dornier, Product
Support, P.O. Box 1103, D-82230 Wessling, Federal Republic of
Germany; telephone: (08153) 300; facsimile: (08153) 302985. This
service information may be examined at the FAA, Central Region,
Office of the Regional Counsel, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
(f) The inspection and replacement required by this AD shall be
done in accordance with Dornier Service Bulletin No. 1140-0000, Date
of Issue: September 29, 1995. 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
Daimler-Benz Aerospace, Dornier, Product Support, P.O. Box 1103, D-
82230 Wessling, Federal Republic of Germany. Copies may be inspected
at the FAA, Central Region, Office of the Regional Counsel, Room
1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of
the Federal Register, 800 North Capitol Street, NW, suite 700,
Washington, DC.
Note 3: The subject of this AD is addressed in German AD 96-271
Daimler-Benz Aerospace/Dornier, Effective Date: October 10, 1996.
(g) This amendment becomes effective on December 28, 1998.
Issued in Kansas City, Missouri, on November 10, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-31009 Filed 11-20-98; 8:45 am]
BILLING CODE 4910-13-P
