[Federal Register Volume 68, Number 139 (Monday, July 21, 2003)]
[Rules and Regulations]
[Pages 42954-42956]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-17945]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-04-AD; Amendment 39-13239; AD 2003-14-20]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 82-12-
06, which applies to certain AeroSpace Technologies of Australia Pty 
Ltd. (ASTA) Models N22B and N24A airplanes. AD 82-12-06 currently 
requires repetitive visual inspections of all rudder control lever 
shaft assemblies for cracks and discrepancies, and, if cracks or 
discrepancies are found, it requires replacement with new or 
serviceable rudder control shafts, and a check of the fit of all rod 
end bearings in lever shafts. AD 82-12-06 also allows you to inspect 
all lever shafts by magnetic particle inspection or dye penetrant 
methods as terminating action for the repetitive visual inspections. 
This AD is the result of recent reports of failures of the upper 
control lever torque shaft due to fatigue loading on the affected 
airplanes, including those that included the terminating actions. This 
AD requires more detailed repetitive inspections (than there are in AD 
82-12-06) of the upper and lower rudder pedal torque shafts and a one-
time inspection for discrepancies in the thickness of the lever shaft 
side plates with appropriate follow-up action. The actions specified by 
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.

DATES: This AD becomes effective on September 8, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
September 8, 2003.

ADDRESSES: You may get the service information referenced 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 this information at the Federal 
Aviation Administration (FAA), Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2003-CE-04-AD, 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.

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

    Has FAA taken any action to this point? 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 currently requires the following on 
certain ASTA Models N22B and N24A airplanes:

--Repetitively inspecting visually all rudder control lever shafts for 
cracking;
--If cracks are found, before further flight, 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.

    What has happened since AD 82-12-06 to initiate this proposed 
action? The Civil Aviation Safety Authority (CASA), which is the 
airworthiness authority for Australia, recently notified FAA of the 
need to change AD 82-12-06. The CASA reports failures of the rudder 
control lever shaft. All the failures have occurred during ground 
operations and nosewheel steering/rudder loads are now considered the 
primary cause of the failure.
    Some of the failures occurred on airplanes where the terminating 
action of AD 82-12-06 was incorporated.
    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 certain ASTA Models N22B and N24A. 
This proposal was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on April 29, 2003 (68 FR 22636). The NPRM 
proposed to require you to repetitively inspect, using either dye 
penetrant or magnetic particle methods and measurements, 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.
    Was the public invited to comment? The FAA encouraged interested 
persons to participate in the making of this amendment. We did not 
receive any comments on the proposed rule or on our determination of 
the cost to the public.

FAA's Determination

    What is FAA's final determination on this issue? After careful 
review of all available information related to the subject presented 
above, we have determined that air safety and the public interest 
require the adoption of the rule as proposed except for minor editorial 
corrections. We have determined that these minor corrections:

--Provide 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.

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, FAA 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 special flight permits, alternative methods of 
compliance, and altered products. 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.

[[Page 42955]]

Cost Impact

    How many airplanes does this AD impact? We estimate that this AD 
affects 10 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 
initial inspection:

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                                                          Total cost per
            Labor cost                   Parts cost          airplane          Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
12 workhours x $60 per hour = $720  Not Applicable......            $720  10 x $720 = $7,200.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary 
repetitive inspections:

------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                   Parts cost          airplane
------------------------------------------------------------------------
2 workhours x $60 per hour = $120.  Not Applicable......            $120
------------------------------------------------------------------------

    We estimate the following costs to accomplish any necessary lever 
shaft replacements that would be required based on the results of the 
proposed inspections. We have no way of determining the number of 
airplanes that may need such replacement:

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                  Labor cost                     Parts cost                 Total cost per airplane
----------------------------------------------------------------------------------------------------------------
12 workhours x $60 per hour = $720...........            $930  $720 + $930 = $1,650.
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    We estimate the following costs to accomplish any necessary lever 
shaft side plate replacements 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 such replacement:

----------------------------------------------------------------------------------------------------------------
                  Labor cost                     Parts cost                 Total cost per airplane
----------------------------------------------------------------------------------------------------------------
12 workhours x $60 per hour = $720...........            $930  $720 + $930 = $1,650.
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Regulatory Impact

    Does this AD impact various entities? The regulations adopted 
herein 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. Therefore, it is determined that this final rule does not 
have federalism implications under Executive Order 13132.
    Does this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this action (1) is not a 
``significant regulatory action'' under Executive Order 12866; (2) is 
not a ``significant rule'' under 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. A copy 
of the final evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

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 removing Airworthiness Directive (AD) 82-
12-06, Amendment 39-4399, and by adding a new AD to read as follows:

2003-14-20 Aerospace Technologies of Australia PTY LTD.: Amendment 
39-13239; Docket No. 2003-CE-04-AD; Supersedes AD 82-12-06, 
Amendment 39-4399.

    (a) What airplanes are affected by this AD? This AD affects 
Models N22B and N24A airplanes, all serial numbers, that are 
certificated in any category.
    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
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.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

[[Page 42956]]



------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Inspect the rudder control    Within the next     In accordance with
 lever shafts, part numbers (P/    100 hours time-in-  Nomad Alert
 N) 2/N-45-1102, 1/N-45-1103,      service (TIS)       Service Bulletin
 and 1/N-45-1104 (or FAA-          after September     ANMD-27-51, dated
 approved equivalent part          8, 2003 (the        September 13,
 numbers) for cracks. Use dye      effective date of   2002, and the
 penetrant while the shaft is      this AD), unless    applicable
 installed; or either dye          already             maintenance
 penetrant inspection or           accomplished.       manual.
 magnetic particle methods if
 the shaft is removed.
(2) Inspect all lever shaft side  Within the next     In accordance with
 plates on P/Ns 2/N-45-1102, 1/N-  100 hours TIS       Nomad Alert
 45-1103, and 1/N-45-1104 (or      after September     Service Bulletin
 FAA-approved equivalent part      8, 2003 (the        ANMD-27-51, dated
 numbers) by measuring the         effective date of   September 13,
 thickness for discrepancies.      this AD), unless    2002, and the
                                   already             applicable
                                   accomplished.       maintenance
                                                       manual.
(3) Visually inspect all rudder   Repetitively        In accordance with
 control lever shafts P/Ns 2/N-    inspect at          Nomad Alert
 45-1102, 1/N-45-1103, and 1/N-    intervals not to    Service Bulletin
 45-1104 (or FAA-approved          exceed 100 hours    ANMD-27-51, dated
 equivalent part numbers) for      TIS after the       September 13,
 cracks.                           inspection          2002, and the
                                   required in         applicable
                                   paragraph (d)(1)    maintenance
                                   of this AD.         manual.
(4) If damage is found during     Prior to further    In accordance with
 any inspection required by this   flight after any    Nomad Alert
 AD.                               inspection          Service Bulletin
                                   required by this    ANMD-27-51, dated
(i) For lever shafts found with    AD.                 September 13,
 crack damage, replace with new                        2002, and the
 or serviceable items.                                 applicable
                                                       maintenance
                                                       manual.
(ii) For discrepancies in the
 thickness of lever shaft side
 plates, obtain a repair scheme
 from the manufacturer through
 FAA at the address specified in
 paragraph (e) of this AD and
 incorporate this repair scheme
(iii) Repairable and
 nonrepairable damage is defined
 in the service information
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way?
    (1) To use an alternative method of compliance or adjust the 
compliance time, follow the procedures in 14 CFR 39.13. Send these 
requests to the Manager, Los Angeles Aircraft Certification Office. 
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.
    (2) Alternative methods of compliance approved in accordance 
with AD 82-12-06, which is superseded by this AD, are not approved 
as alternative methods of compliance with this AD.
    (f) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Nomad Alert Service Bulletin ANMD-27-51, dated September 13, 
2002. The Director of the Federal Register approved this 
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. 
You may get copies 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 copies at the FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (g) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 82-12-06, Amendment 39-4399.

    Note: The subject of this AD is addressed in Australian AD GAF-
N22/44, dated November 14, 2002.

    (h) When does this amendment become effective? This amendment 
becomes effective on September 8, 2003.

    Issued in Kansas City, Missouri, on July 10, 2003.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-17945 Filed 7-18-03; 8:45 am]
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