AD 2004-14-12

[Federal Register Volume 69, Number 131 (Friday, July 9, 2004)]
[Rules and Regulations]
[Pages 41407-41410]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 04-15507]


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DEPARTMENT OF TRANSPORTATION (DOT)

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18032; Directorate Identifier 2004-CE-15-AD; 
Amendment 39-13721; AD 2004-14-12]
RIN 2120-AA64


Airworthiness Directives; The New Piper Aircraft, Inc., Models 
PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-
301FT, PA-32-301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain The New Piper Aircraft, Inc. (Piper), Models PA-28-161, PA-28-
181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-301FT, PA-32-
301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP airplanes. 
This AD requires you to inspect the control wheel attaching hardware 
for proper installation, replace if required, add Loctite thread-
locking compound to the screw installation, and install a retainer clip 
to the control wheel attachment. This AD is the result of inadequate 
control wheel attachment design. The screw used to attach the control 
wheel to the control column is too short in some installations, and the 
nut-plate does not have adequate locking features. In addition, the 
screw is installed from the bottom of the control wheel and will depart 
quickly after thread disengagement. We are issuing this AD to detect 
and correct inadequate control wheel attachment design features, which 
could result in loss of control of the ailerons and elevator. This 
failure could lead to loss of control of the aircraft.

DATES: This AD becomes effective on August 10, 2004.
    As of August 10, 2004, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.
    We must receive any comments on this AD by September 14, 2004.

ADDRESSES: Use one of the following to submit comments on this AD:
    <bullet> DOT Docket web site: Go to <a href="http://dms.dot.gov">http://dms.dot.gov</a> and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a> and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
    <bullet> Fax: 1-202-493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You may get the service information identified in this AD from The 
New Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida, 32960.
    You may view the comments to this AD in the AD docket on the 
Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>.

FOR FURTHER INFORMATION CONTACT: Samuel Belete, Aerospace Safety 
Engineer, FAA Atlanta Certfication Office, One Crown Center, 1895 
Phoenix Boulevard, Suite 450, Atlanta, Georgia, 30349; telephone: (770) 
703-6048; facsimile: (770) 703-6097.

SUPPLEMENTARY INFORMATION: What events have caused this AD? On July 7, 
2003, a Piper PA-28-181 airplane crashed in the desert northeast of

[[Page 41408]]

Phoenix, Arizona, after the pilot lost control of the ailerons and 
elevator. The left control wheel single MS24964-S59 screw backed out of 
its nut plate and caused the control wheel to spin freely on the 
control column. Further investigation revealed the screw was too short 
and the nut plate lacked proper locking features to prevent the screw 
from backing out and becoming disengaged. In addition, the screw was 
installed on the bottom of the control wheel allowing it to fall out 
once it became disengaged. An investigation of sample fleets after the 
incident revealed that a large portion of the sampled airplanes had 
similar problems.
    The following airplanes have a similar type design and would be 
subject to these same conditions: The New Piper Aircraft, Inc., Models 
PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-
301FT, PA-32-301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP 
airplanes.
    What is the potential impact if FAA took no action? Inadequate 
control wheel attaching hardware could result in loss of control of the 
ailerons and elevator. This failure could lead to loss of control of 
the airplane.
    Is there service information that applies to this subject? Yes, The 
New Piper Aircraft, Inc. has issued Service Bulletin No. 1139A, dated 
April 9, 2004.
    What are the provisions of this service information? The service 
bulletin includes procedures for:

--Inspecting the control wheel attachment screw and nut plate for 
proper installation;
--Replacing the screw and/or nut plate, if required;
--Applying Loctite thread-locking compound; and
--Installing a retainer clip under the control wheel shaft assembly.

FAA's Determination and Requirements of the AD

    What has FAA decided? We have evaluated all pertinent information 
and identified an unsafe condition that is likely to exist or develop 
on other products of this same type design.
    Since the unsafe condition described previously is likely to exist 
or develop on other Piper Models PA-28-161, PA-28-181, PA-28R-201, PA-
32R-301 (HP), PA-32R-301T, PA-32-301FT, PA-32-301XTC, PA-34-220T, PA-
44-180, PA-46-350P, and PA-46-500TP airplanes of the same type design, 
we are issuing this AD to detect and correct inadequate control wheel 
attaching hardware, which could result in loss of control of the 
ailerons and elevator. This failure could lead to loss of control of 
the airplane.
    What does this AD require? This AD requires you to incorporate the 
actions in the previously-referenced service bulletin.
    In preparing of this rule, we contacted type clubs and aircraft 
operators to get technical information and information on operational 
and economic impacts. We did not receive any information through these 
contacts. If received, we would have included a discussion of any 
information that may have influenced this action in the rulemaking 
docket.
    How does the revision to 14 CFR part 39 affect this 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.

Comments Invited

    Will I have the opportunity to comment before you issue the rule? 
This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-18032; 
Directorate Identifier 2004-CE-15-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. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it. If a person contacts us through a 
nonwritten communication, and that contact relates to a substantive 
part of this 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 the AD in light of those comments.

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. FAA-2004-18032; Directorate Identifier 2004-CE-15-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 adding the following new airworthiness 
directive (AD):

2004-14-12 The New Piper Aircraft, Inc.: Amendment 39-13721; Docket 
No. FAA-2004-18032; Directorate Identifier 2004-CE-15-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on August 10, 2004.

Are Any Other ADs Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

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

[[Page 41409]]



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                Models                                                Serial Nos.
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(1) Group A:
    (i) PA-28-161 Warrior III........  2842026 through 2842180.
    (ii) PA-28-181 Archer III........  2843112 through 2843565.
    (iii) PA-28R-201 Arrow...........  2844014 through 2844099.
    (iv) PA-32R-301 Saratoga II HP...  3246098 through 3246214.
    (v) PA-32R-301T Saratoga II TC...  3257028 through 3257327.
    (vi) PA-34-220T Seneca V.........  3449042 through 3449292.
    (vii) PA-44-180 Seminole.........  4496020 through 4496173, and 4496175.
    (viii) PA-46-350P Mirage.........  4636132 through 4636344, and
    (ix) PA-46-500TP Meridian........  4697001 through 4697162.
(2) Group B:
    (i) PA-28-161 Warrior III........  2842181 through 2842203.
    (ii) PA-28-181 Archer III........  2843566 through 2843588.
    (iii) PA-28R-201 Arrow...........  2844100 through 2844104.
    (iv) PA-32R-301 Saratoga II HP...  3246215 through 3246219.
    (v) PA-32R-301T Saratoga II TC...  3257328 through 3257340.
    (vi) PA-32-301FT Piper 6X........  3232001 through 3232013.
    (vii) PA-32-301XTC Piper 6XT.....  3255001 through 3255014.
    (viii) PA-34-220T Seneca V.......  3449293 through 3449301.
    (ix) PA-44-180 Seminole..........  4496174 and 4496176 through 4496180.
    (x) PA-46-350P Mirage............  4636345 through 4636348, and
    (xi) PA-46-500TP Meridian........  4697163 through 4697174.
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What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of inadequate control wheel attaching 
hardware. We are issuing this AD to detect and correct inadequate 
control wheel attachment design, which could result in loss of 
control of the ailerons and elevator. This failure could lead to 
loss of airplane.

What Must I Do to Address This Problem?

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

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           Actions                 Compliance            Procedures
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(1) For airplanes listed in   Inspect within 25     Follow Part I of The
 Group A of paragraph (c)(1)   hours Time-in-        New Piper Aircraft,
 of this AD: follow the        Service (TIS) after   Inc., Service
 instructions below, with      the effective date    Bulletin No. 1139,
 the exception of airplanes    of this AD, August    dated April 9,
 listed in Group A that are    10, 2004. Replace     2004.
 already modified in           prior to further
 accordance with The New       flight after the
 Piper Aircraft, Inc.,         inspection.
 Service Bulletin No. 1139,
 dated, August 28, 2003.
(i) Inspect the control
 wheel attachment screw for
 property thread engagement
 (minimum one thread showing
 past the end of the nut
 plate), and replace the
 crew if insufficient thread
 engagement is found.
(ii) Inspect the nut plate
 for sufficient locking
 characteristics (minimum
 one thread showing past the
 nut plate, when the screw
 is tightened by hand), and
 replace the nut plate if it
 is insufficient.
(iii) After the above
 inspections, reassemble the
 control wheel onto the
 control wheel shaft and
 apply Loctite thread-
 locking compound.
(2) For airplanes listed in   Install the retainer  Follow Part II of
 Group A or Group B of         clip within 100       The New Piper
 paragraphs (c)(1) and (2)     hours TIS after the   Aircraft Inc.,
 of this AD: install the       effective date of     Service Bulletin
 retainer clip Part Number     this AD, August 10,   No. 1139A, dated
 104687-002.                   2004.                 April 9, 2004.
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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, Atlanta Aircraft 
Certification Office, FAA. For information on any already approved 
alternative methods of compliance, contact Samuel Belete, Aerospace 
Safety Engineer, FAA Atlanta Certification Office, One Crown Center, 
1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia, 30349; 
telephone: (770) 703-6048; facsimile: (770) 703-6097.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in The New Piper Aircraft, Inc., Service Bulletin No. 
1139A, dated April 9, 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. You may get a 
copy from The New Piper Aircraft, Inc., 2926 Piper Drive, Vero 
Beach, Florida, 32960. You may review copies at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>. You may view the AD docket at the 
Docket Management Facility;

[[Page 41410]]

U.S. Department of Transportation, 400 Seventh Street, SW., Nassif 
Building, Room PL-401, Washington, DC 20590-001.

    Issued in Kansas City, Missouri, on June 29, 2004.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-15507 Filed 7-8-04; 8:45 am]
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