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

[Federal Register Volume 69, Number 42 (Wednesday, March 3, 2004)]
[Rules and Regulations]
[Pages 9927-9930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-4374]



[[Page 9927]]

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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

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