[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]
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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. 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]
BILLING CODE 4910-13-U
