[Federal Register Volume 61, Number 227 (Friday, November 22, 1996)]
[Rules and Regulations]
[Pages 59325-59326]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-29721]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-CE-93-AD; Amendment 39-9831; AD 96-24-05]
RIN 2120-AA64


Airworthiness Directives; Aerospace Technologies of Australia 
Nomad 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 (ASTA) Nomad Models 
N22B, N22S, and N24A airplanes. This action requires inspecting the 
flap and aileron control rod fork ends for water accumulation and 
corrosion inside the internally drilled holes, and replacing the 
control rod fork ends if there is visible corrosion, or sealing the 
hole if no corrosion is found. Reports of water entering the internal 
holes of the flap and aileron control rod fork ends, causing corrosion, 
prompted this AD action. The actions specified by this AD are intended 
to prevent corrosion and water accumulation in the flap and aileron 
control rod fork ends, which, if not detected and corrected, could 
cause loss of control of the flaps and aileron and possible loss of 
control of the airplane.

DATES: Effective January 17, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 17, 1997.

ADDRESSES: Service information that applies to this AD may be obtained 
from Aerospace Technologies of Australia, Limited, ASTA DEFENCE, 
Private Bag No. 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-93-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, Los 
Angeles Aircraft Certification Office, FAA, 3960 Paramount Blvd., 
Lakewood, California, 90712; telephone (310) 627-5224; facsimile (310) 
627-5210.

SUPPLEMENTARY INFORMATION:

Events Leading to This Action

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to ASTA Nomad Models 
N22B, N22S, and N24A airplanes was published in the Federal Register on 
March 14, 1996 (61 FR 10478). The action proposed inspecting the flap 
and aileron control rod fork ends for water accumulation and corrosion 
inside the internally drilled holes, and replacing the control rod fork 
ends if there is visible corrosion or sealing the hole if no corrosion 
is found.

Related Service Information

    Accomplishment of this action would be in accordance with ASTA 
Nomad Service Bulletin (SB) NMD-27-24, dated October 8, 1982.
    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.

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 would be 
affected by this AD, that it would take approximately 3 workhours per 
airplane to accomplish this action, and that the average labor rate is 
approximately $60 an hour. In estimating the total cost impact of this 
AD on U.S. operators, the FAA is only using the inspection criteria (3 
workhours). The FAA has no way of knowing how many airplanes have 
incorporated the modification. With this in mind and based on those 
figures above, the total cost impact of this AD upon U.S. operators of 
the affected airplanes is $2,700. This figure only includes the cost 
for the initial inspection and does not include replacement costs of 
the corroded part. The FAA has no way of determining the number of 
corroded control rod fork ends.

Compliance Time for This AD

    The compliance time of this AD is in calendar time instead of hours 
time-in-service (TIS). The FAA has determined that a calendar time 
compliance is the most desirable method because the unsafe condition 
described by this AD is caused by corrosion. Corrosion initiates as a 
result of airplane operation, but can continue to develop regardless of 
whether the airplane is in service or in storage. Therefore, to ensure 
that the above-referenced condition is detected and corrected on all 
airplanes within a reasonable period of time without inadvertently 
grounding any airplanes, a compliance schedule based upon calendar time 
instead of hours TIS is appropriate.

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

[[Page 59326]]

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:

96-24-05  Aerospace Technologies of Australia (ASTA): Amendment 39-
9831; Docket No. 95-CE-93-AD.

    Applicability: Nomad Models N22B, N22S, and N24A airplanes with 
the following serial numbers, certificated in any category.

Nomad N22B and N22S

N22B-5M, N22B-6M, N22B-7, N22B-11M, N22B-12M, N22B-15M, N22B-16M, 
N22B-18M, N22B-19M, N22B-20M, N22B-21M, N22B-22M, N22B-23M, N22B-25, 
N22B-27, N22B-31M, N22B-33, N22B-35, N22B-37, N22B-50, N22B-53, 
N22B-56, N22B-57, N22B-58, N22B-59, N22B-61, N22B-65M, N22B-66, 
N22B-67M, N22B-68, N22B-69, N22B-70, N22S-82, N22B-83, N22S-84, 
N22B-85M, N22S-86, N22S-87, N22B-88M, N22S-90, N22B-91M, N22S-92, 
N22B-93, N22B-95, N22B-97M, N22B-100M, N22B-102, N22B-103, and N22B-
104

Nomad N24A

N24A-44, N24A-46, N24A-62, N24A-64, N24A-71, N24A-72, N24A-73, N24A-
74, N24A-75, N24A-76, N24A-77, N24A-78, and N24A-79

    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 (e) 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 1 year after the effective 
date of this AD, unless already accomplished.

    To prevent corrosion and water accumulation in the flap and 
aileron control rod fork ends, which, if not detected and corrected, 
could cause loss of control of the flaps and aileron and possible 
loss of control of the airplane, accomplish the following:
    (a) Inspect for corrosion and water accumulation inside the 
internally drilled holes of the flap and aileron control rod fork 
ends in accordance with the Accomplishment Instructions section of 
Nomad Service Bulletin (SB) NMD-27-24, dated October 8, 1982.
    (b) If corrosion is present, prior to further flight, replace 
the control rod fork ends, part number (P/N) 1/N-45-351 or P/N 1/N-
45-1059, and seal the drilled holes in accordance with the 
Accomplishment Instructions section of Nomad SB NMD-27-24, dated 
October 8, 1982.
    (c) If no corrosion is present, prior to further flight, seal 
the drilled holes to prevent future corrosion in accordance with the 
Accomplishment Instructions section of Nomad SB NMD-27-24, dated 
October 8, 1982.
    (d) 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.
    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an equivalent level of safety may be 
approved by the Manager, Los Angeles Aircraft Certification Office, 
FAA, 3960 Paramount Blvd., Lakewood, California. 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.

    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.

    (f) The inspection, modification, or replacement required by 
this AD shall be done in accordance with Nomad Service Bulletin NMD-
27-24, dated October 8, 1982. 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, Limited, 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.
    (g) This amendment (39-9831) becomes effective on January 17, 
1997.

    Issued in Kansas City, Missouri, on November 13, 1996.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-29721 Filed 11-21-96; 8:45 am]
BILLING CODE 4910-13-U