[Federal Register Volume 68, Number 248 (Monday, December 29, 2003)]
[Proposed Rules]
[Pages 74874-74877]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31847]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-43-AD]
RIN 2120-AA64


Airworthiness Directives; AeroSpace Technologies of Australia Pty 
Ltd Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all AeroSpace Technologies of Australia Pty Ltd Model N22B, N22S, 
and N24A airplanes. This proposed AD would require you to inspect the 
forward and aft face of the rear fuselage frame for cracks and to 
repair or modify accordingly. This proposed AD is the result of 
mandatory continuing airworthiness information issued by the 
airworthiness authority for Australia. We are issuing this proposed AD 
to detect and correct cracks in the rear fuselage frame, which could 
result in failure of the fuselage rear bulkhead and consequent loss of 
structural integrity.

DATES: We must receive any comments on this proposed AD by February 2, 
2004.

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. 2000-CE-43-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. 2000-CE-43-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 AeroSpace Technologies of Australia Pty Ltd; 226 Lorimer Street, 
Port Melbourne Victoria 3207, Australia.
    You may view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No.

[[Page 74875]]

2000-CE-43-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, Senior Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone: (562) 627-5224; facsimile: (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

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. 2000-CE-43-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 AeroSpace Technologies of Australia 
Pty Ltd N22 and N24 series airplanes. The CASA received a number of 
reports of airplanes with cracks around the rivet heads on the rear 
bulkhead frame. The cracks could result in failure of the fuselage rear 
bulkhead and consequent loss of airplane control.

What are the consequences if the condition is not corrected?

    We are issuing this proposed AD to detect and correct cracks in the 
rear fuselage frame, which could result in failure of the fuselage rear 
bulkhead and consequent loss of airplane control.

Is there service information that applies to this subject?

    AeroSpace Technologies of Australia Pty Ltd has issued the Nomad 
Alert Service Bulletin--53-15, which incorporates the following pages.

------------------------------------------------------------------------
                                       Revision
           Effective pages              level              Date
------------------------------------------------------------------------
1-31 (reprint of entire service               2  October 6, 1997.
 bulletin).
1 through 4, 13 through 19, and 23            3  June 1, 1999.
 and 24.
------------------------------------------------------------------------

What are the provisions of this service information?

    The service bulletin includes procedures for inspecting the rear 
fuselage bulkhead of aircraft for cracks and making required repairs 
and/or modifications.

What action did the CASA take?

    The CASA classified this service bulletin as mandatory and issued 
Australian AD Number AD/GAF-N22/65 amendment 3, dated May 5, 2000, to 
ensure the continued airworthiness of these airplanes in Australia.

Did the CASA inform the United States per the bilateral airworthiness 
agreement?

    These AeroSpace Technologies of Australia Pty Ltd Model N22B, N22S, 
and N24A airplanes are manufactured in Australia and are 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.
    Under this bilateral airworthiness agreement, the CASA has kept us 
informed of the situation described above.

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 AeroSpace Technologies of Australia Pty Ltd 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 cracks in the rear fuselage frame.

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 14 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:

[[Page 74876]]



----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                  Labor cost                               Parts cost                airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
General Visual Inspection--0.5 work hours est.  No parts needed for inspection..             $30            $420
 $60 per hour = $30.
Detailed Visual Inspection--5 work hours est.   No parts needed for inspection..            $300          $4,200
 $60 per hour = $300.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary repairs 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of airplanes that may need 
these repairs:

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost       airplane
------------------------------------------------------------------------
Repair--20 work hours est. $60 per hour           $1,000          $2,200
 = $1,200...............................
------------------------------------------------------------------------

    We estimate the following costs to accomplish the proposed 
modification:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                           Labor cost                               Parts cost       airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
Modification--24 work hours est. $60 per hour = $1,440..........            $500          $1,940         $27,160
----------------------------------------------------------------------------------------------------------------

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. 2000-CE-43-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. 2000-CE-43-
AD

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

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by February 2, 2004.

What Other ADs Are Affected By This Action?

    (b) None.

What Airplanes Are Affected By This AD?

    (c) This AD affects the following airplane models and line 
sequence numbers (serial numbers) that are certificated in any 
category:

------------------------------------------------------------------------
                  Models                        Line sequence numbers
------------------------------------------------------------------------
(1) N22B and N22S.........................  1 through 9, 11 through 29,
                                             31, 33, 35, 37, 39 through
                                             41, 43, 45, 47 through 59,
                                             61, 63, 65 through 70, 82
                                             through 88, 90 through 95,
                                             97, 100, 102 through 114,
                                             116, 118, 125, 126, 131
                                             through 134, 136 through
                                             138, 141, and 143 through
                                             170.
(2) N24A..................................  10, 30, 32, 34, 36, 38, 42,
                                             44, 46, 60, 62, 64, 71
                                             through 81, 89, 96, 98, 99,
                                             101, 115, 117, 119 through
                                             124, 127 through 130, 135,
                                             139, 140, and 142.
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of reports of cracks around the rivet 
heads on the rear bulkhead frame. The actions specified in this AD 
are intended to detect and correct cracks in the rear fuselage 
bulkhead. The cracks could result in failure of the fuselage rear 
bulkhead and consequent loss of structural integrity.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

[[Page 74877]]



------------------------------------------------------------------------
             Action                   Compliance          Procedures
------------------------------------------------------------------------
(1) Perform a general visual      For airplanes that  Do the inspection
 inspection of the forward face    have not been       following Section
 of the rear fuselage frame for    repaired as         2.A of Nomad
 cracks.                           described in the    Service Bulletin
                                   service bulletin:   ANMD-53-15. (See
                                   Inspect within 50   paragraph (f) of
                                   hours time in       this AD for a
                                   service (TIS)       list of effective
                                   after the           pages.)
                                   effective date of
                                   this AD, if not
                                   already
                                   inspected.
                                   Repetitively
                                   inspect every 100
                                   hours TIS
                                   thereafter until
                                   the modification
                                   in paragraph
                                   (e)(4) of this AD
                                   is done.
                                  For airplanes that
                                   have been
                                   repaired as
                                   described in the
                                   service bulletin:
                                   Inspect within
                                   500 hours TIS
                                   after repair or
                                   next 100 hours
                                   TIS after the
                                   effective date of
                                   this AD,
                                   whichever occurs
                                   later.
                                   Repetitively
                                   inspect every 100
                                   hours TIS
                                   thereafter until
                                   the modification
                                   in paragraph
                                   (e)(4) of this AD
                                   is done.
(2) Perform a detailed visual     For airplanes that  Do the inspection
 inspection of the aft face of     have not been       following Section
 the rear fuselage frame for       repaired as         2.A of Nomad
 cracks.                           described in the    Service Bulletin
                                   service bulletin:   ANMD-53-15. (See
                                   Inspect within      paragraph (f) of
                                   100 hours TIS       this AD for a
                                   after the           list of effective
                                   effective date of   pages.)
                                   this AD.
                                   Repetitively
                                   inspect every 300
                                   hours TIS
                                   thereafter until
                                   the modification
                                   in paragraph
                                   (e)(4) of this AD
                                   is done..
                                  For airplanes that
                                   have been
                                   repaired as
                                   described in the
                                   service bulletin:
                                   Inspect within
                                   500 hours TIS
                                   after repair or
                                   100 hours TIS
                                   after the
                                   effective date of
                                   this AD,
                                   whichever occurs
                                   later.
                                   Repetitively
                                   inspect every 300
                                   hours TIS
                                   thereafter or
                                   until the
                                   modification in
                                   paragraph (e)(4)
                                   of this AD is
                                   done.
(3) Repair any cracks found       If any cracks are   Do repairs
 during any general or detailed    found during a      following Section
 inspection required by this AD.   general or          2.B of Nomad
                                   detailed            Service Bulletin
                                   inspection, the     ANMD-53-15. (See
                                   airplane must be    paragraph (f) of
                                   repaired before     this AD for a
                                   further flight.     list of effective
                                   See compliance      pages.)
                                   for modification
                                   below.
(4) Modify the airplane by        For airplanes that  Do modification
 installing AeroSpace              have not been       following Section
 Technologies of Australia         repaired before     2.C of Nomad
 Modification N806.                the effective       Service Bulletin
                                   date of this AD:    ANMD-53-15. (See
                                   Modification is     paragraph (f) of
                                   mandatory within    this AD for a
                                   100 hours TIS or    list of effective
                                   12 months of the    pages.)
                                   effective date of
                                   this AD,
                                   whichever occurs
                                   sooner.
                                  Modification
                                   terminates the
                                   inspection
                                   requirements of
                                   this AD.
                                  For aircraft that
                                   have been
                                   repaired before
                                   the effective
                                   date of this AD:.
                                  Modification is
                                   mandatory within
                                   3,000 effective
                                   hours TIS after
                                   incorporation of
                                   the repair or 18
                                   months after the
                                   effective date of
                                   this AD,
                                   whichever occurs
                                   later.
                                   Modification
                                   terminates the
                                   inspection
                                   rerquirements of
                                   this AD.
------------------------------------------------------------------------

    (f) The Aerospace Technologies of Australia Pty Ltd has issued 
the Nomad Alert Service Bulletin-53-15, which incorporates the 
following pages.

------------------------------------------------------------------------
                                       Revision
           Effective pages              level              Date
------------------------------------------------------------------------
1-31 (reprint of entire service               2  October 6, 1997
 bulletin).
1 through 4, 13 through 19, and 23            3  June 1, 1999
 and 24.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (g) 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 Ron Atmur, Senior Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone: (562) 627-5224; facsimile: (562) 627-5210. 
For information on any already approved alternative methods of 
compliance, contact Ron Atmur at the above mentioned address.

May I Get Copies of the Documents Referenced in This AD?

    (h) You may get copies of the documents referenced in this AD 
from AeroSpace Technologies of Australia Pty Ltd, 226 Lorimer 
Street, Port Melbourne Victoria 3207, Australia. 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?

    (i) Australian Airworthiness Directive AD/GAF-N22/65 Amdt 3, 
dated May 5, 2000, also addresses the subject of this AD.

    Issued in Kansas City, Missouri, on December 17, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-31847 Filed 12-24-03; 8:45 am]
BILLING CODE 4910-13-P