[Federal Register: March 3, 2004 (Volume 69, Number 42)]
[Rules and Regulations]
[Page 9927-9930]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03mr04-4]
[[Page 9927]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-37-AD; Amendment 39-13494; AD 2004-05-02]
RIN 2120-AA64
Airworthiness Directives; AeroSpace Technologies of Australia Pty
Ltd. Models N22B, N22S, and N24A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) for all
AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N22S,
and N24A airplanes. This AD requires you to repetitively inspect wing
fittings for fatigue defects, replace or correct defective wing
fittings, and replace the stub wing front spar assembly and wing
fitting when fatigue life limits are reached. This AD is the result of
mandatory continuing airworthiness information (MCAI) issued by the
airworthiness authority for Australia. We are issuing this AD to detect
and correct defects in the wing strut upper end fittings, wing strut
lower end fittings, stub wing strut pick up fittings, and the stub wing
front spar assembly. These defects could result in failure of the
fittings or spar assembly and lead to reduced structural capability or
reduced controllability of the airplane.
DATES: This AD becomes effective on April 20, 2004.
As of April 20, 2004, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
ADDRESSES: You may get the service information identified in this AD
from Nomad Operations, Aerospace Support Division, Boeing Australia, PO
Box 767, Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366;
facsimile 61 7 3306 3111.
You may view the AD docket at FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2003-CE-37-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m.
to 4 p.m., Monday through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
What events have caused this AD? The Civil Aviation Safety
Authority (CASA), which is the airworthiness authority for Australia,
recently notified FAA that an unsafe condition may exist on all ASTA
Models N22B, N22S, and N24A airplanes. The CASA reports that fatigue
tests on the wing strut upper end fitting have shown premature failures
and rapid crack growth. Also, fatigue tests on the wing strut lower end
fittings, stub wing strut pick up fitting, and stub wing front spar
assembly have identified appropriate fatigue lives for the respective
parts.
What is the potential impact if FAA took no action? Fatigue loading
could result in failure of the wing strut upper end fitting, wing strut
lower end fittings, stub wing strut pick up fitting, or stub wing front
spar assembly. This failure could lead to reduced structural capability
or reduced controllability of the airplane.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to all ASTA Models N22B, N22S, and N24A
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on October 24, 2003 (68 FR 60887).
The NPRM proposed to require you to repetitively inspect wing fittings
for fatigue defects, replace or correct defective wing fittings, and
replace the stub wing front spar assembly and wing fitting when fatigue
life limits are reached.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in the development of this AD. We received
no comments on the proposal or on the determination of the cost to the
public.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for minor
editorial corrections. We have determined that these minor corrections:
--Are consistent with the intent that was proposed in the NPRM for
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 15 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes?
We estimate the following costs to accomplish the inspection of the
wing strut upper end fitting bolt holes:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
12 workhours x $65 per hour = Not applicable..... $780 15 x $780 = $11,700.
$780.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to accomplish the inspection of the
stub wing strut pick up fittings:
[[Page 9928]]
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
16 workhours x $65 per hour = Not applicable..... $1,040 15 x $1,040 = $15,600.
$1,040.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to accomplish any necessary
replacements of the wing strut upper end fittings that will be required
based on the results of the inspection or on reaching the fatigue life
limit. We have no way of determining the number of airplanes that may
need the replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
10 workhours x $65 per hour = $650.......... $679 $650 + $679 = $1,329.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to accomplish any necessary
replacements of the wing strut lower end fittings that will required
based on reaching the fatigue life limit. We have no way of determining
the number of airplanes that may need the replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
12 workhours x $65 per hour = $780.......... $193 $780 + $193 = $973.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to accomplish any necessary
replacements of the stub wing strut pick up fittings that will be
required based on the results of the inspection or on reaching the
fatigue life limit. We have no way of determining the number of
airplanes that may need the replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
80 workhours x $65 per hour = $5,200........ $985 $5,200 + $985 = $6,185.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to accomplish any necessary
replacements of the stub wing front spar assembly that will be required
based on reaching the fatigue life limit. We have no way of determining
the number of airplanes that may need the replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
370 workhours x $65 per hour = $24,050...... $4,820 $24,050 + $4,820 = $28,870.
----------------------------------------------------------------------------------------------------------------
Regulatory Findings
Will this AD impact various entities? We have determined that this
AD will not have federalism implications under Executive Order 13132.
This AD will not have a substantial direct effect 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.
Will this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2003-CE-37-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under 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
0
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]
0
2. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2004-05-02 Aerospace Technologies of Australia Pty Ltd.: Amendment
39-13494; Docket No. 2003-CE-37-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on April 20, 2004.
What Other ADs Are Affected By This Action?
(b) None.
[[Page 9929]]
What Airplanes Are Affected by This AD?
(c) This AD affects Models N22B, N22S, and N24A airplanes, all
serial numbers, that are certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Australia. The actions specified in this AD are intended to detect
and correct defects in the wing strut upper end fittings, wing strut
lower end fittings, stub wing strut pick up fittings, and the stub
wing front spar assembly. These defects could result in failure of
the fittings or spar assembly and lead to reduced structural
capability or reduced controllability of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the wing strut For Models N22S and Follow the
upper end fitting bolt N24A: Initially Accomplishment
holes: inspect before Instructions in
(i) visually inspect for 3,600 hours time-in- Boeing Australia
scoring, ovality, fretting, service (TIS) on Aerospace
corrosion, and dimensions; the wing strut Technologies of
and upper end fitting Australia Nomad
(ii) inspect, using eddy or within the next Alert Service
current inspection, for 100 hours TIS after Bulletin No. ANMD-
cracks April 20, 2004 (the 57-12, Revision 2,
effective date of dated May 25, 1999.
this AD), whichever
occurs later.
Repetitively
inspect thereafter
every 900 hours TIS
until 14,400 hours
TIS are accumulated
on the wing strut
upper end fitting.
For Model N22B:
Initially inspect
before 5,400 hours
TIS on the wing
strut upper end
fitting or within
the next 100 hours
TIS after April 20,
2004 (the effective
date of this AD),
whichever occurs
later. Repetitively
inspect thereafter
at every1,200 hours
TIS until 14,400
hours TIS are
accumulated on the
wing strut upperend
fitting.
-----------------------------
(2) Complete corrective Before further Follow the
actions for defects of the flight after the Accomplishment
wing strut upper end inspection required Instructions in
fittings: in paragraph (e)(1) Boeing Australia
(i) If a crack is found or of this AD, unless Aerospace
the hole in the strut upper already done. Technologies of
end fitting is damaged and Australia Nomad
will not clean up, replace Alert Service
the wing strut upper end Bulletin No.ANMD-57-
fittings. 12, Revision 2,
(ii) If the hole in the dated May 25, 1999;
strut is oval or damaged, and any repair
and the oversize line scheme obtained
reamer will not repair it: from Nomad
(A) get a repair scheme from Operations,
the manufacturer; and Aerospace Support
(B) follow this repair Division,
scheme. BoeingAustralia, PO
(iii) If scoring, fretting, Box 767, Brisbane,
or corrosion is found, or QLD 4000 Australia;
all dimensions are within telephone 61 73306
limits, line ream the hole 3366; facsimile 61
and replace the bolt 7 3306 3111. Obtain
approval of this
repair scheme
through the FAA at
the address
specified in
paragraph (f) of
this AD.
-----------------------------
(3) Replace the wing strut Before further Follow the
upper end fittings. flight when cracks Accomplishment
are found by the Instructions in
inspection required accumulation Boeing
inparagraph (e)(1); Australia Aerospace
and upon the Technologies of
accumulation of Australia Nomad
14,400 hours TIS on Alert Service
the fitting or Bulletin No. ANMD-
within the next 100 57-12, Revision 2,
hours TIS after dated May 25, 1999.
April 20, 2004 (the
effective date of
this AD), whichever
occurs later. For
Models N22S and
N24A: start
repetitive
inspections of
paragraph (e)(1) of
this AD when 7,200
hours TIS are
accumulated on the
wing strut upper
end fitting. For
Models N22B: start
repetitive
inspections of
paragraph (e)(1) of
this AD when 10,800
hours TIS are
accumulated on the
wing strut upper
end fitting.
-----------------------------
(4) Replace the wing strut Upon the Follow a repair
lower end fittings: accumulation of scheme from Nomad
(i) get a repair scheme from 14,000 hours TIS on Operations,
the manufacturer; and the fitting or Aerospace Support
(ii) follow this repair within the next 100 Division, Boeing
scheme hours TIS after Australia, PO Box
April 20, 2004 (the 767, Brisbane, QLD
effective date of 4000 Australia;
this AD), whichever telephone 61 73306
occurs later. 3366; facsimile 61
7 3306 3111. Get
approval of this
repair scheme
through the FAA at
the address
specified in
paragraph (f) of
this AD.
-----------------------------
[[Page 9930]]
(5) Inspect the stub wing Initially inspect Follow the
strut pick up fittings for upon the Accomplishment
cracks accumulation of Instructions in
5,400 hours TIS on Aerospace
the fitting or Technologies of
within the next 300 Australia Nomad
hours TIS on the Service Bulletin
fitting after April No. NMD-53-18,
20, 2004 (the dated February 8,
effective date of 1996; or Boeing
this AD), whichever Australia Aerospace
occurs later. Technologies of
Repetitively Australia
inspect thereafter NomadService
at every 1,800 Bulletin No. NMD-53-
hours TIS until 18, Revision 1,
18,800 hours TIS dated September 3,
are accumulated on 2002; and the
the stub wing strut applicable airplane
pick up fitting. maintenance manual.
-----------------------------
(6) Replace the stub wing Before further Follow the
strut pick up fittings flight when cracks Accomplishment
are found after the Instructions in
inspection required Aerospace
in paragraph (e)(5) Technologies of
of this AD, unless Australia Nomad
already done; and Service Bulletin
upon the No. NMD-53-18,
accumulation of dated February 8,
18,800 hours TIS or 1996; or Boeing
300 hours TIS after Australia Aerospace
April 20, 2004 (the Technologies of
effective date of Australia Nomad
this AD), whichever Service Bulletin
occurs later. No. NMD-53-18,
Revision 1, dated
September 3, 2002;
and the applicable
airplane
maintenance manual.
-----------------------------
(7) Replace the stub wing Upon the Follow a repair
front spar assembly: accumulation of scheme from Nomad
(i) get a repair scheme from 25,000 hours TIS on Operations,
the manufacturer; and the wing strut Aerospace Support
(ii) follow this repair upper end fitting, Division, Boeing
scheme wing strut lower Australia, PO Box
end fitting, or 767, Brisbane, QLD
stub wing strut 4000 Australia;
pick up fitting, or telephone 61 73306
within the next 100 3366; facsimile 61
hours TIS after 7 3306 3111. Get
April 20, 2004 (the approval of this
effective date of repair scheme
his AD), whichever through the FAA at
occurs later. the address
specified in
paragraph (f) of
this AD.
------------------------------------------------------------------------
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Los Angeles Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, contact Ron Atmur,
Aerospace Engineer, FAA, Los Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood, California 90712; telephone
(562) 627-5224; facsimile (562) 627-5210.
Does This AD Incorporate Any Material by Reference?
(g) You must do the actions required by this AD following the
instructions in Boeing Australia Aerospace Technologies of Australia
Nomad Alert Service Bulletin No. ANMD-57-12, Revision 2, dated May
25, 1999; Aerospace Technologies of Australia Nomad Service Bulletin
No. NMD-53-18, dated February 8, 1996; and Boeing Australia
Aerospace Technologies of Australia Nomad Service Bulletin No. NMD-
53-18, Revision 1, dated September 3, 2002. The Director of the
Federal Register approved the incorporation by reference of this
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. You may get a copy from Nomad Operations, Aerospace Support
Division, Boeing Australia, P.O. Box 767, Brisbane, QLD 4000
Australia; telephone 61 7 3306 3366; facsimile 61 7 3306 3111. You
may review copies at FAA, Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
Is There Other Information That Relates to This Subject?
(h) These Australian ADs also address the subject of this AD: AD
Number AD/GAF-N22/2, Amendment 3, dated January 28, 2003, and AD
Number AD/GAF-N22/70, Amendment 2, dated January 28, 2003.
Issued in Kansas City, Missouri, on February 20, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-4374 Filed 3-2-04; 8:45 am]
BILLING CODE 4910-13-P