[Federal Register Volume 62, Number 103 (Thursday, May 29, 1997)]
[Rules and Regulations]
[Pages 28997-28999]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-14077]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-98-AD; Amendment 39-10041; AD 97-11-12]
RIN 2120-AA64
Airworthiness Directives; Aerospace Technologies of Australia Pty
Ltd. (Formerly Government Aircraft Factory) Models N22B, N22S, and N24A
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 Aerospace Technologies of Australia Pty Ltd. (ASTA) Models
N22B, N22S, and N24A airplanes. This action requires repetitively
inspecting the stub wing upper front spar cap flanges for cracks, and
repairing any cracked part. This AD results from fatigue tests that
show that the stub wing upper front spar cap flanges could fail over
time because of fatigue. The actions specified by this AD are intended
to prevent structural failure of the front spar caused by cracks in the
stub wing upper front spar cap flanges, which could result in loss of
control of the airplane.
DATES: Effective July 11, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 11, 1997.
ADDRESSES: Service information that applies to this AD may be obtained
from Aerospace Technologies of Australia Pty Ltd., ASTA DEFENCE,
Private Bag No.
[[Page 28998]]
4, Beach Road Lara 3212, Victoria, Australia. This information may also
be examined at the Federal Aviation Administration (FAA), Central
Region, Office of the Assistant Chief Counsel, Attention: Rules Docket
95-CE-98-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. Ron Atmur, Aerospace Engineer,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712; telephone (562) 627-5224;
facsimile (562) 627-5210.
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 ASTA Models N22B,
N22S, and N24A airplanes was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on December 10, 1996 (61 FR
65002). The NPRM proposed to require repetitively inspecting the stub
wing upper front spar cap flanges for cracks, and repairing any cracked
part. Accomplishment of the proposed inspections as specified in the
NPRM would be in accordance with Nomad Service Bulletin NMD-53-6, dated
October 21, 1986. Accomplishment of any proposed repair (if necessary)
as specified in the NPRM would be in accordance with a scheme obtained
from the FAA, Los Angeles Aircraft Certification Office.
The NPRM resulted from fatigue tests that show that the stub wing
upper front spar cap flanges could fail over time because of fatigue.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed AD 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.
Cost Impact
The FAA estimates that 15 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 6 workhours per
airplane to accomplish the required action, and that the average labor
rate is approximately $60 an hour. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $5,400 or
$360 per airplane. This figure does not take into account the cost of
repetitive inspections or the cost to repair any cracked stub wing
upper front spar cap flanges. The FAA has no way of determining the
number of repetitive inspections each operator will incur over the life
of each affected airplane or the number of stub wing upper front spar
cap flanges that may be found cracked and need to be repaired.
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
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:
97-11-12 Aerospace Technologies of Australia PTY LTD: Amendment 39-
10041; Docket No. 95-CE-98-AD.
Applicability: Models N22B, N22S, and N24A airplanes (all serial
numbers), certified 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, alternation, 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 structural failure of the front spar caused by cracks
in the stub wing upper front spar cap flanges, which would result in
loss of control of the airplane, accomplish the following:
(a) Prior to accumulating 1,700 hours time-in-service (TIS) or
within the next 300 hours TIS after the effective date of this AD,
whichever occurs later, and thereafter at intervals not to exceed
2,650 hours TIS, inspect, using both visual and eddy current
methods, the stub wing front spar cap flanges in the area of Buttock
Line (BL) 47.6 for fatigue cracks in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Nomad Service Bulletin NMD-
53-6, dated October 21, 1986.
(b) If any crack is found during any inspection required by this
AD, prior to further flight, obtain a repair scheme from the
manufacturer through the Los Angeles Aircraft Certification Office
(ACO) at the address specified in paragraph (d) of this AD, and
incorporate this repair scheme. This repair does not eliminate the
repetitive inspection requirement of this AD.
(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 time that provides an equivalent level of safety may be
approved by the Manager, FAA, Los Angeles ACO, 3960 Paramount
Boulevard, Lakewood,
[[Page 28999]]
California 90172. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Los Angeles ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
(e) The inspections required by this AD shall be done in
accordance with Nomad Service Bulletin NMD-53-6, dated October 21,
1986. 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 Aerospace Technologies of
Australia Pty Ltd., ASTA DEFENCE, Private Bag No. 4, Beach Road Lara
3212, Victoria, Australia. Copies may be inspected at the FAA,
Central Region, Office of the Assistant Chief 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.
(f) This amendment (39-10041) becomes effective on July 11,
1997.
Issued in Kansas City, Missouri, on May 22, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-14077 Filed 5-28-97; 8:45 am]
BILLING CODE 4910-13-U
