[Federal Register Volume 61, Number 249 (Thursday, December 26, 1996)]
[Proposed Rules]
[Pages 67965-67967]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-32850]


 ========================================================================
 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.
 
 ========================================================================
 

  Federal Register / Vol. 61, No. 249 / Thursday, December 26, 1996 / 
Proposed Rules  

[[Page 67965]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-31-AD]
RIN 2120 AA64


Airworthiness Directives; AeroSpace Technologies of Australia 
Limited (formerly Government Aircraft Industries), Nomad Models N22S, 
N22B, and N24A Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to supersede AD 82-25-09 which 
currently requires repetitively inspecting the pilot and co-pilot 
control wheel sub-assemblies for cracks, and if cracked, modifying the 
cracked part on the AeroSpace Technologies of Australia, Limited 
(ASTA), formerly Government Aircraft Industries (GAF) Nomad Models 
N22S, N22B, and N24A airplanes. The proposed action would retain the 
repetitive inspection of the pilot and co-pilot control wheel sub-
assemblies for cracks, but would include a modification that would 
terminate the repetitive inspections by replacing or re-working the 
control wheel sub-assembly with a part of improved design. This 
proposed superseding action is prompted by cracking in the control 
wheel sub-assemblies and the manufacture of an improved part that would 
terminate the repetitive inspection. The actions specified by the 
proposed AD are intended to prevent failure of the pilot's and co-
pilot's control wheels, which, if not detected and corrected, could 
result in loss of control of the airplane.

DATES: Comments must be received on or before February 21, 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-31-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-31-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-31-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Discussion

    Airworthiness Directive 82-25-09, Amendment 39-4510 currently 
requires repetitively inspecting the pilot and co-pilot control wheel 
sub-assemblies for cracks, and if cracked, modifying the cracked part 
on the ASTA Nomad Models N22S, N22B, and N24A airplanes. Accomplishment 
of the proposed modification would terminate the repetitive 
inspections.

Actions Since Issuance of Previous Rule

    The Civil Aviation Safety Authority (CASA) of Australia, which is 
the airworthiness authority for Australia, notified the FAA that an 
unsafe condition may exist on ASTA Nomad Models N22S, N22B, and N24A 
airplanes. The CASA of Australia advises that several incidents have 
been reported of the pilot's and co-pilot's control wheels developing 
structural cracks and becoming inoperable, reducing the pilots' ability 
to control the airplane during flight.
    Since the publication of AD 82-25-09, the manufacturer has designed 
a part of improved design. The proposed action would retain the 
repetitive inspection of the pilot and co-pilot control wheel sub-
assemblies for cracks, but would include a modification that would 
terminate the repetitive inspections by replacing or re-working the 
control wheel sub-assembly with a part of improved design.

Applicable Service Information

    ASTA has issued Government Aircraft Factories (GAF) Nomad Alert 
Service Bulletin (SB) AS/B ANMD-27-27, Revision 1, dated November 5, 
1982, which specifies repetitively inspecting the control wheel sub-
assemblies for cracking, modifying the assemblies by replacing or 
reworking them when cracks appear, and upon the accumulation of 300 
hours time-in-service, modifying the control wheel sub-assemblies by 
replacing or re-working them with a part of improved design. This 
modification would be

[[Page 67966]]

considered a terminating action for the repetitive inspections.
    The CASA of Australia classified this service bulletin as mandatory 
and issued CASA of Australia AD/GAF-N22/46 AMDT 1 in order to assure 
the continued airworthiness of these airplanes in Australia.

FAA's Determination

    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 this 
bilateral airworthiness agreement, the Australian CASA has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of the Australian 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 Provision of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other ASTA Nomad Models N22S, N22B, and N24A 
airplanes of the same type design registered for operation in the 
United States, the proposed AD would supersede AD 82-25-09 with a new 
AD that would retain the repetitive 100 hour time-in-service (TIS) 
inspections for cracks on the pilot's and co-pilot's control wheel sub-
assembly (part number (P/N) 1/N-45-1208) in the area adjacent to the 
circumferential weld adjoining the shaft spigot to each control wheel 
back support plate, modifying any cracked assembly by replacing the 
assembly with a part of improved design (P/N 2/N-45-1208), or re-
working the assembly with approved re-worked parts (P/N 1/N-03-734), 
and if there are no signs of cracking during these inspections, 
terminating the repetitive inspections upon the accumulation of 300 
hours TIS by accomplishing the modification to control wheel sub-
assemblies with parts of improved design. This modification would be 
considered a terminating action for the repetitive inspections required 
in AD 82-25-09.

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 6 
workhours per airplane to accomplish the proposed action, and that the 
average labor rate is approximately $60 an hour. Parts cost 
approximately $1,592 per airplane. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$23,680 or $1,952 per airplane. This figure is based on the cost of the 
initial inspection and modification and does not account for the 
repetitive inspections that may occur prior to the proposed 
modification. The FAA has no way to determine the number of airplanes 
that may have already accomplished this action.

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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13   [Amended]

    2. Section 39.13 is amended by removing Airworthiness Directive 
(AD) 82-25-09, Amendment 39-4510, and by adding a new AD to read as 
follows:
Aerospace Technologies of Australia, Limited (ASTA) (formerly 
Government Aircraft Industries (GAF)):
    Docket No. 95-CE-31-AD; Supersedes AD 82-25-09, Amendment 39-
4510.
    Applicability: Nomad Models N22S, N22B, and N24A 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 (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 the next 100 hours time-in-service 
(TIS) after the effective date of this AD, and thereafter as 
indicated in this AD, unless already accomplished.

    To prevent failure of the pilot's and co-pilot's control wheels, 
which, if not detected and corrected, could result in loss of 
control of the airplane, accomplish the following:
    (a) Inspect the pilot and co-pilot control wheel sub-assembly 
(part number (P/N) 1/N-45-1208) for structural cracking in the area 
adjacent to the circumferential weld adjoining the shaft spigot to 
each control wheel back support plate in accordance with the ``2. 
Accomplishment Instructions'' section, ``Part A--Inspection'' 
paragraphs in Government Aircraft Industries (GAF) Nomad Alert 
Service Bulletin (SB) AS/B ANMD-27-27, Revision 1, dated November 5, 
1982.
    (1) If no cracks are visible, repetitively inspect the control 
wheel sub-assemblies at intervals not to exceed 100 hours TIS in 
accordance with the ``2. Accomplishment Instructions'' section, 
``Part A--Inspection'' paragraphs in GAF Nomad Alert Service 
Bulletin (SB) AS/B ANMD-27-27, Revision 1, dated November 5, 1982 
until the accomplishment of paragraph (b) of this AD.
    (2) If cracks are visible during any inspection required by this 
AD, prior to further flight, modify the control wheel sub-assemblies 
by replacing or re-working the cracked part with parts of improved 
design (P/N 2/N-45-1208 or 1/N-03-734 (reworked part)) in accordance 
with the ``2. Accomplishment Instructions'' section, ``Part B--
Modification by Replacement or Rework'' paragraphs in GAF Nomad 
Alert SB AS/B ANMD-27-27, Revision 1, dated November 5, 1982.
    (b) Upon the accumulation of 300 hours TIS after the effective 
date of this AD, modify the control wheel sub-assemblies (P/N 1/N-
45-1208) by replacing the assemblies or re-working the assemblies 
with parts of improved design (P/N 2/N-45-1208 or P/N 1/N-03-734, 
respectively) in accordance

[[Page 67967]]

with the ``2. Accomplishment Instructions'' section, ``Part B--
Modification by Replacement or Rework'' paragraphs in GAF Nomad 
Alert SB AS/B ANMD-27-27, Revision 1, dated November 5, 1982.
    (c) Accomplishment of the modification in paragraph (b) of this 
AD is considered a terminating action for the repetitive inspections 
required in paragraph (a)(1) of this AD.
    (d) Special flight permits may be issued in accordance with 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 
initial or repetitive 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 82-
25-09 (superseded by this action) are considered approved as 
alternative methods of compliance with 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.

    (f) All persons affected by this directive may obtain copies of 
the document referred to herein upon request to 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.
    (g) This amendment supersedes AD 82-25-09, Amendment 39-4510.

    Issued in Kansas City, Missouri, on December 18, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-32850 Filed 12-24-96; 8:45 am]
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