[Federal Register Volume 68, Number 206 (Friday, October 24, 2003)]
[Proposed Rules]
[Pages 60887-60891]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-26899]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-37-AD]
RIN 2120-AA64


Airworthiness Directives; AeroSpace Technologies of Australia Pty 
Ltd. Models N22B, N22S, and N24A Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models 
N22B, N22S, and N24A airplanes. This proposed AD would 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. This 
proposed AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for Australia. 
We are issuing this proposed 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: We must receive any comments on this proposed AD by December 4, 
2003.

ADDRESSES: Use one of the following to submit comments on this proposed 
AD:
    [sbull] By mail: FAA, Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2003-CE-37-AD, 901 Locust, Room 
506, Kansas City, Missouri 64106.
    [sbull] By fax: (816) 329-3771.
    [sbull] By e-mail: [email protected]. Comments sent 
electronically must contain ``Docket No. 2003-CE-37-AD'' in the subject 
line. If you send comments electronically as attached electronic files, 
the files must be formatted in Microsoft Word 97 for Windows or ASCII.
    You may get the service information identified in this proposed 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:

[[Page 60888]]

Comments Invited

    How do I comment on this proposed AD? We invite you to submit any 
written relevant data, views, or arguments regarding this proposal. 
Send your comments to an address listed under ADDRESSES. Include ``AD 
Docket No. 2003-CE-37-AD'' in the subject line of your comments. If you 
want us to acknowledge receipt of your mailed comments, send us a self-
addressed, stamped postcard with the docket number written on it. We 
will date-stamp your postcard and mail it back to you.
    Are there any specific portions of this proposed AD I should pay 
attention to? We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of this 
proposed AD. If you contact us through a nonwritten communication and 
that contact relates to a substantive part of this proposed AD, we will 
summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend this 
proposed AD in light of those comments and contacts.

Discussion

    What events have caused this proposed 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 are the consequences if the condition is not corrected? 
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. Such failure could lead to 
reduced structural capability or reduced controllability of the 
airplane.
    Is there service information that applies to this subject? Boeing 
Australia (formerly ASTA) Aerospace Technologies of Australia has 
issued:

--Nomad Alert Service Bulletin No. ANMD-57-12, Revision 2, dated May 
25, 1999;
--Nomad Service Bulletin No. NMD-53-18, dated February 8, 1996; and
--Nomad Service Bulletin No. NMD-53-18, Revision 1, dated September 3, 
2002.
    What are the provisions of this service information? The service 
bulletins include procedures for:

--Performing a fatigue inspection of the stub wing strut pick-up 
fittings for cracks;
--Replacing the stub wing strut pick-up fittings;
--Inspecting (visually) the strut to upper strut fittings bolt holes 
for scoring, ovality, fretting, corrosion, and dimensions;
--Inspecting (eddy current method) the strut to upper strut fittings 
bolt holes for cracks;
--Modifying (line ream) the strut to upper strut fitting bolt holes;
--Replacing bolts for the strut upper end fittings; and
--Replacing the strut upper end fittings.

    What action did the CASA take? The CASA classified these service 
bulletins as mandatory and issued these Australian ADs in order to 
ensure the continued airworthiness of these airplanes in Australia:

--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.

FAA's Determination and Requirements of This Proposed AD

    What has FAA decided? We have examined the CASA's findings, 
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.
    Since the unsafe condition described previously is likely to exist 
or develop on other ASTA Models N22B, N22S, and N24A airplanes of the 
same type design that are registered in the United States, we are 
proposing AD action 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 would this proposed AD require? This proposed AD would require 
you to incorporate the actions in the previously-referenced service 
bulletin.
    How does the revision to 14 CFR part 39 affect this proposed AD? On 
July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs 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 would this proposed AD impact? We estimate that 
this proposed AD affects 15 airplanes in the U.S. registry.
    What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to 
accomplish the proposed inspection of the wing strut upper end fitting 
bolt holes:

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                                                                   Total cost per
              Labor cost                       Parts cost             airplane      Total cost on U.S. operators
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12 workhours x $65 per hour = $780....  Not applicable..........             $780           15 x $780 = $11,700
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    We estimate the following costs to accomplish the proposed 
inspection of the stub wing strut pick up fittings:

----------------------------------------------------------------------------------------------------------------
                                                                   Total cost per
              Labor cost                       Parts cost             airplane      Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
16 workhours x $65 per hour = $1,040..  Not applicable..........           $1,040         15 x $1,040 = $15,600
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[[Page 60889]]

    We estimate the following costs to accomplish any necessary 
replacements of the wing strut upper end fittings that would be 
required based on the results of the proposed inspection or on reaching 
the fatigue life limit. We have no way of determining the number of 
airplanes that may need such replacement:

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                           Labor cost                                Parts cost       Total cost per  airplane
----------------------------------------------------------------------------------------------------------------
10 workhours x $65 per hour = $650..............................             $679          $650 + $679 = $1,329
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    We estimate the following costs to accomplish any necessary 
replacements of the wing strut lower end fittings that would be 
required based on reaching the fatigue life limit. We have no way of 
determining the number of airplanes that may need such replacement:

----------------------------------------------------------------------------------------------------------------
                           Labor cost                                Parts cost        Total cost per airplane
----------------------------------------------------------------------------------------------------------------
12 workhours x $65 per hour = $780..............................             $193            $780 + $193 = $973
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    We estimate the following costs to accomplish any necessary 
replacements of the stub wing strut pick up fittings that would be 
required based on the results of the proposed inspection or on reaching 
the fatigue life limit. We have no way of determining the number of 
airplanes that may need such replacement:

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                           Labor cost                                Parts cost        Total cost per airplane
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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 would be 
required based on reaching the fatigue life limit. We have no way of 
determining the number of airplanes that may need such replacement:

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                           Labor cost                                Parts cost        Total cost per airplane
----------------------------------------------------------------------------------------------------------------
370 workhours x $65 per hour = $24,050..........................           $4,820    $24,050 + $4,820 = $28,870
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Regulatory Findings

    Would this proposed AD impact various entities? We have determined 
that this proposed AD would not have federalism implications under 
Executive Order 13132. This proposed AD would 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.
    Would this proposed AD involve a significant rule or regulatory 
action? For the reasons discussed above, I certify that this proposed 
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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

AeroSpace Technologies of Australia Pty Ltd.: Docket No. 2003-CE-37-
AD

When Is the Last Date I Can Submit Comments on This Proposed AD 
Action?

    (a) We must receive comments on this proposed airworthiness 
directive (AD) action by December 4, 2003.

Are Any Other ADs Affected by This Action?

    (b) None.

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 accomplish the following:

[[Page 60890]]



------------------------------------------------------------------------
           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.                       the effective date    57-12, Revision 2,
                               of this AD,           dated May 25, 1999.
                               whichever occurs
                               later. Repetitively
                               inspect thereafter
                               at 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 the
                               effective date of
                               this AD, whichever
                               occurs later.
                               Repetitively
                               inspect thereafter
                               at every 1,200
                               hours TIS until
                               14,400 hours TIS
                               are accumulated on
                               the wing strut
                               upper end 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               Technologies of
 end fitting is damaged and    accomplished.         Australia Nomad
 will not clean up, replace                          Alert Service
 the wing strut upper end                            Bulletin No. ANMD-
 fittings.                                           57-12, 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, Boeing
 scheme..                                            Australia, PO Box
(iii) If scoring, fretting,                          767, Brisbane, QLD
 or corrosion is found, or                           4000 Australia;
 all dimensions are within                           telephone 61 7 3306
 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   Boeing Australia
                               in paragraph          Aerospace
                               (e)(1); and upon      Technologies of
                               the 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 the   dated May 25, 1999.
                               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 the   Australia, PO Box
                               effective date of     767, Brisbane, QLD
                               this AD, whichever    4000 Australia;
                               occurs later.         telephone 61 7 3306
                                                     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.
(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 the     No. NMD-53-18,
                               effective date of     dated February 8,
                               this AD, whichever    1996; or Boeing
                               occurs later.         Australia Aerospace
                               Repetitively          Technologies of
                               inspect thereafter    Australia Nomad
                               at every 1,800        Service Bulletin
                               hours TIS until       No. NMD-53-18,
                               18,800 hours TIS      Revision 1, dated
                               are accumulated on    September 3, 2002;
                               the stub wing strut   and the applicable
                               pick up fitting.      airplane
                                                     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               Service Bulletin
                               accomplished; and     No. NMD-53-18,
                               upon the              dated February 8,
                               accumulation of       1996; or Boeing
                               18,800 hours TIS or   Australia Aerospace
                               300 hours TIS after   Technologies of
                               the effective date    Australia Nomad
                               of this AD,           Service Bulletin
                               whichever occurs      No. NMD-53-18,
                               later.                Revision 1, dated
                                                     September 3, 2002;
                                                     and the applicable
                                                     airplane
                                                     maintenance manual.

[[Page 60891]]

 
(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 fitting or        Aerospace Support
(ii) Follow this repair        within the next 100   Division, Boeing
 scheme..                      hours TIS after the   Australia, PO Box
                               effective date of     767, Brisbane, QLD
                               this AD, whichever    4000 Australia;
                               occurs later.         telephone 61 7 3306
                                                     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.
------------------------------------------------------------------------

What About Alternative Methods 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 39.13. Send your request to the Manager, Los Angeles Aircraft 
Certification Office, 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.

How Do I Get Copies of the Documents Referenced in This AD?

    (g) You may get copies of the documents referenced 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 these documents at FAA, 
Central Region, Office of the Regional Counsel, 901 Locust, Room 
506, Kansas City, Missouri 64106.

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 October 20, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-26899 Filed 10-23-03; 8:45 am]
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