[Federal Register Volume 70, Number 98 (Monday, May 23, 2005)]
[Rules and Regulations]
[Pages 29437-29440]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-9976]



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  Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and 
Regulations  

[[Page 29437]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20439; Directorate Identifier 2005-CE-04-AD; 
Amendment 39-14102; AD 2005-10-24]
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) to supersede 
AD 2003-14-20, which applies to all AeroSpace Technologies of Australia 
Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 2003-14-20 requires 
you to repetitively inspect, using either dye penetrant or magnetic 
particle methods, the rudder control lever shafts for cracks; inspect 
(one-time) all lever shaft side plates by measuring the thickness; and 
if cracks or discrepancies in thickness are found, replace 
unserviceable parts with new or serviceable parts. Since AD 2003-14-20 
was issued, we determined that the AD should also affect Model N22S 
airplanes. The manufacturer has also revised the service information to 
include a rudder control lever shaft part number (P/N) that was not 
part of AD 2003-14-20. Consequently, this AD retains the actions of AD 
2003-14-20, adds Model N22S airplanes to the applicability, and adds 
rudder control lever shaft P/N 1/N-45-1102 to the inspection 
requirements. We are issuing this AD to detect and correct cracks in 
the rudder control lever torque shafts and discrepancies in the 
thickness of the lever shaft side plates, which could result in failure 
of the rudder control lever torque shaft. Such failure could lead to 
reduced controllability of the airplane.

DATES: This AD becomes effective on June 30, 2005.
    As of June 30, 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 Nomad Operations, Aerospace Support Division, Boeing Australia, 
PO Box 767, Brisbane, QLD 4001 Australia; telephone 61 7 3306 3366; 
facsimile 61 7 3306 3111.
    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-2005-20439; Directorate 
Identifier 2005-CE-04-AD.

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? Reports of cracking and other 
discrepancies on rudder control lever shaft assemblies on certain ASTA 
Models N22B and N24A airplanes caused us to issue AD 82-12-06, 
Amendment 39-4399. AD 82-12-06 required the following:

--Repetitively inspecting visually all rudder control lever shafts for 
cracking;
--If cracks are found, replacing with new or serviceable rudder control 
shafts;
--Checking for clearance of the fit of all rod end bearings in lever 
shafts; and
--Discontinuing the repetitive visual inspections when lever shafts are 
inspected either by magnetic particle inspection or dye penetrant 
methods

    The Civil Aviation Safety Authority (CASA), which is the 
airworthiness authority for Australia notified FAA of the need to 
change AD 82-12-06. The CASA reported failures of the rudder control 
lever shaft. All the failures occurred during ground operations. 
Nosewheel steering/rudder loads are considered the primary cause of the 
failures.
    Some of the failures occurred on airplanes where the terminating 
action of AD 82-12-06 had been incorporated. This caused us to issue AD 
2003-14-20, Amendment 39-13239 (68 FR 42954, July 21, 2003).
    AD 2003-14-20 currently requires the following on all ASTA Model 
N22B and N24A airplanes:

--Repetitively inspecting, using either dye penetrant or magnetic 
particle methods and measurements, certain rudder control lever shafts, 
part numbers (P/N) 2/N-45-1102, 1/N-45-1103, and 1/N-45-1104 (or FAA-
approved equivalent part numbers), for cracks;
--Inspecting (one-time) all lever shaft side plates by measuring the 
thickness; and
--If cracks or discrepancies in thickness are found, replacing 
unserviceable parts with new or serviceable parts.

    What has happened since AD 2003-14-20 to initiate this action? 
Since AD 2003-14-20 was issued, we determined that Model N22S airplanes 
should be included in the applicability.
    The manufacturer has also revised the service information to 
include a rudder control lever shaft P/N that was not part of AD 2003-
14-20.
    What is the potential impact if FAA took no action? This condition, 
if not detected and corrected, could result in failure of the rudder 
control lever torque shaft. Such failure could lead to 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 Model N22B, N22S, and N24A 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on March 16, 2005 (70 FR 12819). 
The NPRM proposed to supersede AD 2003-14-20 with a new AD that would 
retain the actions of AD 2003-14-20, add Model N22S airplanes to the 
applicability, and add rudder control lever shaft P/N 1/N-45-1102 to 
the inspection requirements.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. We

[[Page 29438]]

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 do the initial 
inspection:

----------------------------------------------------------------------------------------------------------------
                                                                   Total cost
           Labor cost                       Parts cost            per 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 do the necessary repetitive 
inspections:

----------------------------------------------------------------------------------------------------------------
                                                                                               Total cost per
                  Labor cost                                    Parts cost                        airplane
----------------------------------------------------------------------------------------------------------------
2 workhours x $65 per hour = $130.............  Not Applicable...........................                 $130.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any rudder control lever 
shaft replacement that will be required based on the results of the 
inspections. 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...........               $930   $780 + $930 = $1710.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any lever shaft side plate 
replacements that will be required based on the results of the 
inspection. 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...........               $930   $780 + $930 = $1710.
----------------------------------------------------------------------------------------------------------------

    What is the difference between the cost impact of this AD and the 
cost impact of AD 2003-14-20? The only difference between AD 2003-14-20 
and this AD is the addition of Model N22S airplanes to the 
applicability section. There are no additional actions required in this 
AD.

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

[[Page 29439]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) 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-2005-20439; Directorate Identifier 2005-CE-04-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. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2003-14-20, Amendment 39-13239 (68 FR 42954, July 21, 2003), and by 
adding a new AD to read as follows:

2005-10-24 Aerospace Technologies of Australia Pty Ltd.: Amendment 
39-14102; Docket No. FAA-2005-20439; Directorate Identifier 2005-CE-
04-AD; Supersedes AD 2003-14-20, Amendment 39-13239.

When Does This AD Become Effective?

    (a) This AD becomes effective on June 30, 2005.

What Other ADs Are Affected By This Action?

    (b) This AD supersedes AD 2003-14-20, Amendment 39-13239.

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 continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Australia. The actions specified in this AD are intended to detect 
and correct cracks in the rudder control lever torque shafts and 
discrepancies in the thickness of the lever shaft side plates, which 
could result in failure of the rudder control lever torque shaft. 
Such failure could lead to 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 following:    Initially inspect     Following Nomad
(i) The rudder control level   within the next 50    Alert Service
 shafts, part numbers (P/N)    hours time-in-        Bulletin ANMD-27-
 1/N-45-1102, 2/N-45-1102, 1/  service (TIS) or 30   51, Rev. 2, dated
 N-45-1103, and 1/N-45-1104    days after June 30,   April 29, 2004, and
 (or FAA-approved equivalent   2005 (the effective   the applicable
 part numbers) for cracks.     date of this AD),     maintenance manual.
 Use dye penetrant             whichever occurs
 inspection while the shaft    first, unless
 is installed. Use either      already done.
 dye penetrant or magnetic
 particle inspection if the
 shaft is removed; and
(ii) All lever shaft side
 plates on P/Ns 1/N-45-1102,
 2/N-45-1102, 1/N-45-1103,
 and 1/N-45-1104 (or FAA-
 approved equivalent part
 numbers) by measuring the
 thickness for
 discrepancies.
(2) If no cracks are found    Repetitively inspect  Following Nomad--
 in the rudder control lever   thereafter at         Series N22 & N24
 shafts during the             intervals not to      Inspection
 inspection required in        exceed 300 hours      Requirements
 paragraph (e)(1)(i) of this   TIS after the         Manual, Temporary
 AD, repetitively inspect      initial inspection    Revision 26,
 rudder control lever shafts   required in           Fatigue Critical
 P/Ns 1/N-45-1102, 2/N-45-     paragraph (e)(1) of   Areas, dated May
 1102, 1/N-45-1103, ands 1/N-  this AD.              27, 2004.
 45-1104 (or FAA-approved
 equivalent part numbers)
 for cracks.
(3) If cracks or              Before further        Following Nomad
 discrepancies are found       flight after any      Alert Service
 during any inspection         inspection required   Bulletin ANMD-27-
 required by this AD, do the   by this AD in which   51, Rev. 2, dated
 following:                    cracks or             April 29, 2004, and
(i) For rudder control lever   discrepancies are     the applicable
 shafts found with crack       found..               maintenance manual.
 damage, replace with new or
 serviceable parts. After
 replacement, continue with
 the repetitive inspections
 required in paragraph
 (e)(2) of this AD..
(ii) If the thickness of the
 lever shaft side plates is
 less than 0.050 inches,
 replace the lever shaft
 side plate with a new plate
 that measures at least
 0.050 inches in thickness..
(4) If at any time certain    Before further        Following Nomad--
 operating conditions occur    flight.               Series N22 & N24
 that caused abnormal rudder                         Inspection
 pedal loads, inspect the                            Requirements
 rudder control lever shafts                         Manual, Temporary
 as specified in paragraph                           Revision 26,
 (e)(2) of this AD. Examples                         Fatigue Critical
 of such conditions are:                             Areas, dated May
 heavy use of nosewheel                              27, 2004.
 steering over rough ground;
 excessive steering angle
 under towl; towing with
 rudder gust lock fitted;
 engine failure on takeoff;
 and aircraft left parked
 outside with rudder gust
 lock not fitted.

[[Page 29440]]

 
(5) Do not install a new      As of June 30, 2005   As specified in
 lever shaft side plate that   (the effective date   Nomad Alert Service
 is less than 0.050 inches     of this AD).          Bulletin ANMD-27-
 in thickness.                                       51, Rev. 2, dated
                                                     April 29, 2004; and
                                                     Nomad--Series N22 &
                                                     N24 Inspection
                                                     Requirements
                                                     Manual, Temporary
                                                     Revision 26,
                                                     Fatigue Critical
                                                     Areas, dated May
                                                     27, 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.
    (1) 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, Rm 301, 
Kansas City, Missouri, 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090.
    (2) Alternative methods of compliance approved for AD 2003-14-20 
are not considered approved as alternative methods of compliance for 
this AD.

Is There Other Information That Relates to This Subject?

    (g) Australian AD GAF-N22/44, Amendment 2, dated November 2004, 
also addresses 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 Nomad--Series N22 & N24 Inspection Requirements 
Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27, 
2004, and Nomad Alert Service Bulletin ANMD-27-51, Rev. 2, dated 
April 29, 2004, which incorporates the following pages:

------------------------------------------------------------------------
                                     Revision
               Pages                  level               Date
------------------------------------------------------------------------
1 and 3...........................          2  April 29, 2004.
2.................................          2  Jan. 29, 2004.
4.................................        \1\  Sept. 13, 2002.
------------------------------------------------------------------------
\1\ Original issue.

    (1) The Director of the Federal Register approved the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) To get a copy of this service information, contact Nomad 
Operations, Aerospace Support Division, Boeing Australia, PO Box 
767, Brisbane, QLD 4001 Australia; telephone 61 7 3306 3366; 
facsimile 61 7 3306 3111. 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-2005-20439; 
Directorate Identifier 2005-CE-04-AD.

    Issued in Kansas City, Missouri, on May 13, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-9976 Filed 5-20-05; 8:45 am]
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