[Federal Register Volume 69, Number 62 (Wednesday, March 31, 2004)]
[Rules and Regulations]
[Pages 16775-16778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6417]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-CE-43-AD; Amendment 39-13536; AD 2004-06-10]
RIN 2120-AA64


Airworthiness Directives; AeroSpace Technologies of Australia Pty 
Ltd Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts a new airworthiness directive (AD) for all 
AeroSpace Technologies of Australia Pty Ltd Model N22B, N22S, and N24A 
airplanes. This AD requires you to inspect the forward and aft face of 
the rear fuselage frame for cracks and to repair or modify accordingly. 
This AD is the result of mandatory continuing airworthiness information 
issued by the airworthiness authority for Australia. We are issuing 
this 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: This AD becomes effective on April 28, 2004.
    As of April 28, 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 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. 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:

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 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 Is the Potential Impact If FAA Took No Action?

    If not detected and corrected, cracks in the rear fuselage frame 
could cause the fuselage rear bulkhead to fail. This failure could 
result in loss of airplane control.

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 
AeroSpace Technologies of Australia Pty Ltd Model N22B, N22S, and N24A 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on December 29, 2003 (68 FR 
74874). The NPRM proposed to require you to inspect the rear fuselage 
bulkhead of aircraft for cracks and make required repairs and/or 
modifications.

Comments

Was the Public Invited To Comment?

    We provided the public the opportunity to participate in developing 
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 the changes discussed above and minor editorial corrections. 
We have determined that these changes and 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 14 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:

----------------------------------------------------------------------------------------------------------------
                                                                                         Total cost   Total cost
                  Labor cost                                  Parts cost                    per        on U.S.
                                                                                          airplane    operators
----------------------------------------------------------------------------------------------------------------
General Visual Inspection--0.5 work hours x     No parts needed for inspection........          $30         $420
 $60 per hour = $30.

[[Page 16776]]

 
Detailed Visual Inspection--5 work hours x $60  No parts needed for inspection........          300        4,200
 per hour = $300.
----------------------------------------------------------------------------------------------------------------

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

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

    We estimate the following costs to accomplish the modification.

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

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. 2000-CE-43-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:

2004-06-10--Aerospace Technologies of Australia Pty Ltd: Amendment 
39-13536; Docket No. 2000-CE-43-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on April 28, 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 No.
------------------------------------------------------------------------
(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 16777]]



----------------------------------------------------------------------------------------------------------------
                 Actions                                  Compliance                          Procedures
----------------------------------------------------------------------------------------------------------------
(1) Perform a general visual inspection    For airplanes that have not been          Do the inspection following
 of the forward face of the rear fuselage   repaired as described in the service      Section 2.A of Nomad
 frame for cracks.                          bulletin: Inspect within 50 hours time    Service Bulletin ANMD-53-
                                            in service (TIS) after April 28, 2004     15. (See paragraph (f) of
                                            (the effective date of this AD), if not   this AD for a list of
                                            already inspected. Repetitively inspect   effective pages.)
                                            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
                                            April 28, 2004 (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 inspection   For airplanes that have been repaired as  Do the inspection following
 of the aft face of the rear fuselage       described in the service bulletin:        Section 2.A of Nomad
 frame for cracks.                          Inspect within 500 hours TIS after        Service Bulletin ANMD-53-
                                            repair or 100 hours TIS after April 28,   15. (See paragraph (f) of
                                            2004 (the effective date of this AD),     this AD for a list of
                                            whichever occurs later. Repetitively      effective pages.)
                                            inspect every 300 hours TIS thereafter
                                            or until the modification in paragraph
                                            (e)(4) of this AD is done.
------------------------------------------
(3) Repair any cracks found during any     If any cracks are found during a general  Do repairs following
 general or detailed inspection required    or detailed inspection, the airplane      Section 2.B of Nomad
 by this AD.                                must be repaired before further flight.   Service Bulletin ANMD-53-
                                            See compliance for modification below.    15. (See paragraph (f) of
                                                                                      this AD for a list of
                                                                                      effective pages.)
------------------------------------------
(4) Modify the airplane by installing      For airplanes that have not been          Do modification following
 AeroSpace Technologies of Australia        repaired before the effective date of     Section 2.C of Nomad
 Modification N806.                         this AD: Modification is mandatory        Service Bulletin ANMD-53-
                                            within 100 hours TIS or 12 months after   15. (See paragraph (f) of
                                            April 28, 2004 (the effective date of     this AD for a list of
                                            this AD), whichever occurs first.         effective pages.)
                                            Modification terminates the inspection
                                            requirements of this AD.
                                           For aircraft that have been repaired
                                            before the effective date of t his AD:
                                            Modification is mandatory within 3,000
                                            hours TIS after incorporation of the
                                            repair or 18 months after April 28,
                                            2004 (the effective date of this AD),
                                            whichever occurs later. Modification
                                            terminates the inspection requirements
                                            of this AD.
----------------------------------------------------------------------------------------------------------------

    (f) The Aerospace Technologies of Australia Pty Ltd has issued 
the Nomad Alert Service Bulletin ANMD-53-15, which incorporates the 
pages as specified in paragraph (h) of this AD.

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 39.19. 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, 
Senior Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 90712-
4137; telephone: (562) 627-5224; facsimile: (562) 627-5210.

Does This AD Incorporate Any Material by Reference?

    (h) You must do the actions required by this AD following the 
instructions in Nomad Alert Service Bulletin ANMD-53-15, effective 
pages as follows:

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

    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 AeroSpace 
Technologies of Australia Pty Ltd, 226 Lorimer Street, Port 
Melbourne Victoria 3207, Australia. 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.

[[Page 16778]]

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 March 17, 2004.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-6417 Filed 3-30-04; 8:45 am]
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