[Federal Register Volume 61, Number 235 (Thursday, December 5, 1996)]
[Proposed Rules]
[Pages 64489-64491]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-30798]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 61, No. 235 / Thursday, December 5, 1996 /
Proposed Rules
[[Page 64489]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-100-AD]
RIN 2120-AA64
Airworthiness Directives; Aerospace Technologies of Australia,
Nomad N22 and N24 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede AD 85-21-06, which
currently requires replacing the attachment fittings of the upper fin
rear spar and the fin/horizontal stabilizer on all Aerospace
Technologies of Australia (ASTA), Nomad N22 and N24 series airplanes.
The proposed action would require removing the upper fin to stub fin
forward attachment bolts, inspecting the attachment fittings for
cracks, and, if no cracks are found, replacing the attachment bolts
with bolts of improved design until the life limit of the attachment
fittings is reached, at which time the attachment fittings would be
replaced. If cracks are found, the proposed action would require
replacing the attachment bolts and attachment fittings. Cracks found in
the underhead radius and at the base of the thread of the bolt prompted
the proposed AD action. The actions specified by the proposed AD are
intended to prevent cracking in the upper fin and horizontal stabilizer
attachment fittings, which if not corrected, could result in loss of
control of the airplane.
DATES: Comments must be received on or before February 3, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-CE-100-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106. Comments may be inspected at
this location between 8 a.m. and 4 p.m., Monday through Friday,
holidays excepted.
Service information that applies to the proposed AD may be obtained
from AeroSpace Technologies of Australia, Limited, ASTA DEFENCE,
Private Bag No. 4, Beach Road Lara 3212, Victoria, Australia. This
information also may be examined at the Rules Docket at the address
above.
FOR FURTHER INFORMATION CONTACT: Mr. Ron Atmur, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, 3960 Paramount Blvd.,
Lakewood, California 90712; telephone (310) 627-5224; facsimile (310)
627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 95-CE-100-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 95-CE-100-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
Discussion
The Civil Aviation Safety Authority (CASA), which is the
airworthiness authority for Australia, recently notified the FAA that
an unsafe condition may exist on ASTA Nomad N22 and N24 series
airplanes. CASA advises that fatigue cracks have been found in the
attachment bolt as well as the attachment fitting of the upper fin and
horizontal stabilizer.
AD 85-21-06 mandated a life limit of 3,000 total hours time-in-
service to these attachment fittings and at that time the attachment
fittings should be replaced in accordance with ASTA Service Bulletin
NMD-53-5, dated October 19, 1984. As a result of cracks being found
during routine inspections prior to the life limit, ASTA advises that
the attachment fittings may crack before that time because of increased
fatigue caused by failure or partial failure of the attachment bolts.
Therefore, the proposed action would supersede AD 85-21-06 by requiring
replacement of the old attachment bolt with a bolt of improved design
to assist in preventing cracks in the attachment fitting before
reaching the life limit, at which time the attachment fittings would be
replaced.
Applicable Service Information
ASTA has issued Nomad Alert Service Bulletin ANMD 55-23, Revision
1, dated July 11, 1991, which specifies inspecting the attach bolt for
cracks and replacing the bolt if cracked, and continue to repetitively
inspect until 3,000 hours time-in-service (TIS). Service Bulletin ANMD
55-23, Revision 1 then specifies accomplishment of Nomad Service
Bulletin (SB) NMD-53-5 Rev. 2, dated December 6, 1995, which specifies
inspecting the attachment bolts and attachment fittings for cracks, and
replacing the attachment bolts and attachment fittings if cracked, or
upon the accumulation of 3,000 hours TIS.
FAA's Conclusion
This airplane model is manufactured in Australia and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to
[[Page 64490]]
this bilateral airworthiness agreement, CASA has kept the FAA informed
of the situation described above. The FAA has examined the findings of
CASA, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Explanation of the Requirements of the Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop in other ASTA Nomad N22 and N24 series airplanes of
the same type design registered for operation in the United States, the
proposed AD would supersede AD 85-21-06 with a new AD that would
require removing the attachment bolt, part number (P/N) 2/N-00-43, and
inspecting the attachment fitting for cracks using a dye penetrant
method. If no cracks are found, the proposed AD would require replacing
the bolt with a new bolt, P/N 3/N-00-43, and, at the accumulation of
3,000 total hours time-in-service (TIS), replacing the attachment
fittings. If cracks are found, the proposed action would require
replacing the attachment bolts and attachment fittings at the time of
inspection and prior to further flight.
Cost Impact
The FAA estimates that 15 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 8
workhours per airplane to accomplish the proposed inspection and bolt
replacement, and that the average labor rate is approximately $60 an
hour. Parts cost approximately $236 per airplane. Based on these
figures, the total cost impact of the proposed AD on U.S. operators is
estimated to be $10,740 or $716 per airplane. The cost of replacing the
attachment fittings is not included in these figures because AD 85-21-
06 previously accounted for the cost of the attachment fitting
replacement.
Regulatory Impact
The regulations proposed herein would 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
accordance with Executive Order 12612, it is determined that this
proposal would 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) if promulgated,
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 draft regulatory evaluation
prepared for this action has been placed 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Airworthiness Directive
(AD) 85-21-06, Amendment 39-5152, and by adding a new AD to read as
follows:
Aerospace Technologies of Australia (ASTA): Docket No. 95-CE-100-AD;
Supersedes AD 85-21-06, Amendment 39-5152.
Applicability: Nomad N22 and N24 series 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 within the next 100 hours time-in-service
(TIS) after the effective date of this AD, unless AD 85-21-06 or
this AD has already been accomplished.
To prevent cracking in the upper fin and horizontal stabilizer
attachment fittings, which if not corrected, could result in loss of
control of the airplane, accomplish the following:
(a) Remove the attachment bolt (part number (P/N) 2/N-00-43, qty
2) and inspect the attachment bolt, vertical fin attachment
fittings, and fin/horizontal stabilizer fittings for cracks, using a
dye penetrant method, in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section in Nomad Alert Service Bulletin (ASB) ANMD-55-
23, Revision 1, dated July 11, 1991.
(1) If no cracks are found, prior to further flight, replace the
attachment bolts (P/N 2/N-00-43, qty 2) with new attachment bolts
(P/N 3/N-00-43, qty 2) in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section in Nomad ASB ANMD-55-23, Revision 1, dated July
11, 1991.
(2) If cracks are found, prior to further flight, replace the
attachment bolts in accordance with the ACCOMPLISHMENT INSTRUCTIONS
section in Nomad ASB 55-23, Revision 1, dated July 11, 1991, and
replace the vertical fin attachment fittings and fin/horizontal
stabilizer fittings in accordance with Nomad Service Bulletin (SB)
NMD-53-5, Revision 2, dated December 6, 1995.
(b) Upon the accumulation of 3,000 hours total TIS, unless
previously accomplished in accordance with paragraph (a)(2) of this
AD, replace the vertical fin attachment fittings and the fin/
horizontal stabilizer fittings in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section in Nomad SB NMD-53-5, Revision 2, dated
December 6, 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
compliance times that provides an equivalent level of safety may be
approved by the Manager, Los Angeles Aircraft Certification Office,
FAA, 3960 Paramount Blvd., Lakewood, California, 90712. The request
shall be forwarded through an appropriate FAA Maintenance Inspector,
who may add comments and then send it to the Manager, Los Angeles
Aircraft Certification Office. Alternative methods of compliance
approved in accordance with AD 85-21-06 are considered approved as
alternative methods of compliance for this AD.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles Aircraft Certification Office.
(e) All persons affected by this directive may obtain copies of
the document referred to herein upon request from AeroSpace
Technologies of Australia, Limited, ASTA DEFENCE, Private Bag No. 4,
Beach Road Lara 3212, Victoria, Australia; or may examine this
document at the FAA, Central Region, Office of the Assistant Chief
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
(f) This amendment supersedes AD 85-21-06, Amendment 39-5152.
[[Page 64491]]
Issued in Kansas City, Missouri, on November 25, 1996.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-30798 Filed 12-4-96; 8:45 am]
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