[Federal Register Volume 70, Number 19 (Monday, January 31, 2005)]
[Rules and Regulations]
[Pages 4761-4763]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-1511]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19442; Directorate Identifier 2004-CE-31-AD; 
Amendment 39-13956; AD 2005-01-11]
RIN 2120-AA64


Airworthiness Directives; Gippsland Aeronautics Pty. Ltd. Model 
GA8 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
Gippsland Aeronautics Pty. Ltd. Model GA8 airplanes. This AD requires 
you to inspect the pilot and co-pilot control column wheels and aileron 
cable operating arm shafts for damage and, if damage is found, to 
repair the shafts or to replace the steel shafts with bronze shafts. We 
are issuing this AD to detect and correct damage of the pilot and co-
pilot control wheels and aileron cable operating arm shafts. This 
damage could result in the aileron controls becoming stiff or locking, 
which could lead to loss of control of the airplane.

DATES: This AD becomes effective on March 4, 2005.
    As of March 4, 2005, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulation.

ADDRESSES: To get the service information identified in this AD, 
contact Gippsland Aeronautics Pty. Ltd., Latrobe Regional Airport, P.O. 
Box 881, Morwell, Victoria 3840, Australia; telephone: 61 (0) 3 5172 
1200; facsimile: 61 (0) 3 5172 1201. To review this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at NARA, 
go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030.
    To view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19442.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, 
Small Airplane Directorate, ACE-112, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: 816-329-4059; facsimile: 816-329-4090.

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 certain 
Gippsland Aeronautics Pty. Ltd. Model GA8 airplanes. CASA reports three 
occurrences of aileron control stiffness and one occurrence of aileron 
control locking during taxi. Rubbing between the control wheel shaft 
and the bush in the control column may cause wear or damage to the 
control wheel shaft where the shaft connects to the control column. 
This damage may lead to the aileron control becoming stiff or locking.
    What is the potential impact if FAA took no action? Damage of the 
pilot and co-pilot control wheels and aileron cable operating arm 
shafts could result in the aileron controls becoming stiff or locking, 
which could lead to loss of control 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 certain Gippsland Aeronautics Pty. 
Ltd. Model GA8 airplanes. This proposal was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on November 8, 2004 
(69 FR 64695). The NPRM proposed to detect and correct damage of the 
pilot and co-pilot control wheels and aileron cable operating arm 
shafts that could result in

[[Page 4762]]

the aileron controls becoming stiff or locking, which could lead to 
loss of control of the airplane.

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 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 5 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  per   Total cost  on
                          Labor cost                              Parts cost        airplane     U.S.  operators
----------------------------------------------------------------------------------------------------------------
2 work hours x $65 per hour = $130...........................             N/A             $130             $650
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
replacements that would be required based on the results of this 
inspection. We have no way of determining the number of airplanes that 
may need this repair/replacement:

----------------------------------------------------------------------------------------------------------------
               Labor cost                          Parts cost                   Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
Labor Cost per side (either pilot or co-  Warranty...................  Per side = $520.
 pilot)--8 work hours x $65 per hour =                                 For both sides = $1,040.
 $520.
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Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106 describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this AD.

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 
``Docket No. FAA-2004-19442; Directorate Identifier 2004-CE-31-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:

2005-02-11 Gippsland Aeronautics Pty. Ltd.: Amendment 39-13956; 
Docket No. FAA-2004-19442; Directorate Identifier 2004-CE-31-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on March 4, 2005.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects model GA8 airplanes, serial numbers GA8-00-
004 through GA8-04-056, that are certificated in any category.

[[Page 4763]]

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of rubbing between the control wheel 
shaft and the bush in the control column, which may cause wear or 
damage to the control wheel shaft where the shaft connects to the 
control column. This damage may lead to the aileron control becoming 
stiff or locking. The actions specified in this AD are intended to 
detect and correct damage of the pilot and co-pilot control wheels 
and aileron cable operating arm shafts that could result in the 
aileron controls becoming stiff or locking, which could lead to loss 
of control 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 pilot and co-     Perform the         Follow Gippsland
 pilot control column wheel and    initial             Aeronautics Pty.
 aileron cable operating arm       inspection within   Ltd. Service
 shafts for damage.                50 hours time-in-   Bulletin SB-GA8-
                                   service (TIS)       2004-11, Issue 2,
                                   after March 4,      dated August 25,
                                   2005 (the           2004.
                                   effective date of
                                   this AD).
(2) If no damage is found,        Perform repetitive  Follow Gippsland
 continue repetitive inspections.  inspections every   Aeronautics Pty.
                                   300 hours TIS       Ltd. Service
                                   until steel         Bulletin SB-GA8-
                                   operating arm       2004-11, Issue 2,
                                   shafts are          dated August 25,
                                   replaced with       2004.
                                   bronze operating
                                   arm shafts.
                                   Replacement of
                                   steel operating
                                   arm shafts with
                                   bronze operating
                                   arm shafts is
                                   terminating
                                   action for this
                                   AD on the side
                                   that was
                                   replaced. If one
                                   steel shaft
                                   requires
                                   replacement, all
                                   of the shafts on
                                   that side (pilot
                                   or co-pilot) must
                                   be replaced with
                                   bronze shafts. If
                                   only one side
                                   (pilot or co-
                                   pilot) is
                                   replaced,
                                   repetitive
                                   inspections are
                                   still required
                                   for the side that
                                   was not replaced.
(3) For airplanes where damage    If damage is        Follow Gippsland
 is found:                         found, repair or    Aeronautics Pty.
(i) If damage can be repaired by   replace operating   Ltd. Service
 polishing out marks or            arm shafts prior    Bulletin SB-GA8-
 scratches so that material        to further          2004-11, Issue 2,
 removed does not exceed 0.005     flight. If          dated August 25,
 inches, repair the shaft. You     airplane is         2004.
 can not repair by polishing out   repaired,
 marks or scratches more than      repetitively
 one time..                        inspect every 300
(ii) If damage can not be          hours TIS after
 repaired by polishing out marks   repair until
 or scratches so that that         replacement of
 material removed does not         the operating arm
 exceed 0.005 inches or you have   shafts.
 already repaired the damage by    Replacement of
 polishing out marks or            the steel
 scratches previously, the damed   operating arm
 steel operating arm shaft must    shafts with
 be replaced with a bronze         bronze operating
 operating arm shaft. When a       arm shafts is
 shaft (pilot or co-pilot)         terminating
 requires replacement, you must    action for this
 install new bronze shafts in      AD. If only one
 all areas of the affected side.   side (pilot or co-
                                   pilot) is
                                   replaced with
                                   bronze shafts,
                                   you must still
                                   repetitively
                                   inspect the other
                                   side that was not
                                   replaced.
(4) As of the effective date of   As of March 4,      Follow Gippsland
 this AD, do not install shafts    2005 (the           Aeronautics Pty.
 that are not bronze on any        effective date of   Ltd. Service
 affected Model GA8 airplane.      this AD).           Bulletin SB-GA8-
                                                       2004-11, Issue 2,
                                                       dated August 25,
                                                       2004.
------------------------------------------------------------------------

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, Standards Office, Small 
Airplane Directorate, FAA. For information on any already approved 
alternative methods of compliance, contact Doug Rudolph, Aerospace 
Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: 816-329-4059; facsimile: 
816-329-4090.

Is There Other Information That Relates to This Subject?

    (g) Australian Civil Aviation Safety Authority Airworthiness 
Directive AD/GA8/2, dated September 17, 2004, and Gippsland 
Aeronautics Pty., Ltd., Service Bulletin SB-GA8-2004-11, dated 
August 25, 2004, also address the subject of this AD.

Does This AD Incorporate Any Material by Reference?

    (h) You must do the actions required by this AD following the 
instructions in Gippsland Aeronautics Pty. Ltd. Service Bulletin SB-
GA8-2004-11, Issue 2, dated August 25, 2004. 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. To get a copy of this service information, contact Gippsland 
Aeronautics Pty. Ltd., Latrobe Regional Airport, P.O. Box 881, 
Morwell, Victoria 3840, Australia; telephone: 61 (0) 3 5172 1200; 
facsimile: 61 (0) 3 5172 1201. To review copies of this service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To 
view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif 
Building, Room PL-401, Washington, DC 20590-001 or on the Internet 
at http://dms.dot.gov. The docket number is FAA-2004-19442.

    Issued in Kansas City, Missouri, on January 20, 2005.
David A. Downey,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-1511 Filed 1-28-05; 8:45 am]
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