Document ID: FAA-2009-1015-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Piper Aircraft, Inc. PA-28, PA-32, PA-34 and PA-44 Series Airplanes
Posted Date: 2009-10-30T04:00Z

[Federal Register: October 30, 2009 (Volume 74, Number 209)]
[Proposed Rules]               
[Page 56138-56140]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30oc09-22]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================

[[Page 56138]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1015; Directorate Identifier 2009-CE-039-AD]
RIN 2120-AA64

 
Airworthiness Directives; Piper Aircraft, Inc. PA-28, PA-32, PA-
34 and PA-44 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Piper Aircraft, Inc. (Piper) PA-28, PA-32, PA-34 and PA-44 
series airplanes. This proposed AD would require an inspection of the 
control wheel shaft for both the pilot and copilot sides and, if 
necessary, replacement of the control wheel shaft. This proposed AD 
results from two field reports of incorrectly assembled control wheel 
shafts. We are proposing this AD to detect and correct any incorrectly 
assembled control wheel shafts. This condition, if left uncorrected, 
could lead to separation of the control wheel shaft, resulting in loss 
of pitch and roll control.

DATES: We must receive comments on this proposed AD by December 29, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; 
telephone: (772) 567-4361; fax: (772) 978-6573; Internet: http://
www.newpiper.com/company/publications.asp.

FOR FURTHER INFORMATION CONTACT: Hector Hernandez, Aerospace Engineer, 
Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, 
College Park, GA 30337; telephone: (404) 474-5587; fax: (404) 474-5606.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2009-1015; Directorate Identifier 2009-CE-039-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    We have received two reports of control wheel shafts that have been 
incorrectly assembled at Piper. The first incident concerned the loss 
of the control wheel on a Piper Model PA-34-220T airplane, where the 
right-hand control wheel shaft and universal joint separated due to a 
misdrilled hole for the threaded taper pin. The second report was of a 
ground inspection on a Piper PA-34-220T airplane that revealed a 
similar situation between the control wheel shaft and the universal 
joint in the left-hand side. Investigation following these reports 
revealed that the control wheel shafts had been incorrectly assembled 
at Piper and holes were misdrilled even though they may visually appear 
acceptable. The hole in the shaft may be too close to the end of the 
shaft, causing a significant reduction in joint strength. Since 
discovery of this problem, Piper has added a step to the manufacturing 
process and also introduced a fixture to ensure proper assembly of the 
control wheel shaft/universal joint.
    This condition, if not corrected, could result in separation of the 
control wheel shaft, resulting in loss of pitch and roll control.

Relevant Service Information

    We have reviewed Piper Aircraft, Inc. Service Bulletin No. 1197A, 
dated September 1, 2009.
    The service information describes procedures for:
     Inspection on both the pilot and copilot control wheel 
columns; and
     If necessary, replacement of the control wheel shaft and 
the universal joint.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would require a mandatory inspection of the control wheel shaft for 
both the pilot and copilot sides. This proposed AD results from two 
field reports of incorrectly assembled control wheel shafts. We are 
proposing this AD to detect and correct any incorrectly assembled 
control wheel shafts. This condition, if left uncorrected, could lead 
to separation of the control wheel shaft, resulting in loss of pitch 
and roll control.

Costs of Compliance

    We estimate that this proposed AD would affect 41,928 airplanes in 
the U.S. registry.
    We estimate the following costs to do the proposed inspection:

[[Page 56139]]

----------------------------------------------------------------------------------------------------------------
                                                                              Total cost per     Total cost on
                 Labor cost                            Parts cost                airplane        U.S. operators
----------------------------------------------------------------------------------------------------------------
0.5 work-hour x $80 per hour = $40.........  Not applicable...............               $40         $1,677,120
----------------------------------------------------------------------------------------------------------------

     We estimate the following costs to do any necessary 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 
this repair/replacement:

------------------------------------------------------------------------
                                                         Total cost per
            Labor cost                  Parts cost          airplane
------------------------------------------------------------------------
16 work-hours x $80 per hour =                  $150             $1,430
 $1,280...........................
------------------------------------------------------------------------

Authority for This Rulemaking

    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 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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.
    For the reasons discussed above, I certify that the proposed 
regulation:
    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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at http://www.regulations.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5527) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Piper Aircraft, Inc.: Docket No. FAA-2009-1015; Directorate 
Identifier 2009-CE-039-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by December 29, 2009.

Affected ADs

    (b) None.

Applicability

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

------------------------------------------------------------------------
                Models                             Serial Nos.
------------------------------------------------------------------------
PA-28-140.............................  28-20001 through 28-26946 and 28-
                                         7125001 through 28-7725290.
PA-28-150.............................  28-03; 28-1 through 28-4377; and
                                         28-1760A.
PA-28-160.............................  28-03; 28-1 through 28-4377; and
                                         28-1760A.
PA-28-180.............................  28-03; 28-671 through 28-5859;
                                         and 28-7105001 through 28-
                                         7205318.
PA-28S-160............................  28-1 through 28-1760 and 28-
                                         1760A.
PA-28S-180............................  28-671 through 28-5859 and 28-
                                         7105001 through 28-7105234.
PA-28-235.............................  28-10001 through 28-11378; 28-
                                         7110001 through 28-7210023; 28E-
                                         11 and 28-7310001 through 28-
                                         7710089.
PA-28-236.............................  28-7911001 through 28-8611008
                                         and 2811001 through 2811050.
PA-28-151.............................  28-7415001 through 28-7715314.
PA-28-161.............................  2841001 through 2841365; 28-
                                         7716001 through 28-8216300; 28-
                                         8316001 through 28-8616057;
                                         2816001 through 2816109;
                                         2816110 through 2816119; and
                                         2842001 through 2842305.
PA-28-180.............................  28-E13 and 28-7305001 through 28-
                                         7505260.
PA-28-181.............................  28-7690001 through 28-8690056;
                                         28-8690061; 28-8690062; 2890001
                                         through 2890205; 2890206
                                         through 2890231; and 2843001
                                         through 2843672.
PA-28-201T............................  28-7921001 through 28-7921095.
PA-28R-180............................  28R-30002 through 28R-31270 and
                                         28R-7130001 through 28R-
                                         7130013.
PA-28R-200............................  28R-35001 through 28R-35820; 28R-
                                         7135001 through 28R-7135229;
                                         and 28R-7235001 through 28R-
                                         7635545.

[[Page 56140]]

PA-28R-201............................  28R-7737002 through 28R-7837317;
                                         2837001 through 2837061; and
                                         2844001 through 2844138.
PA-28R-201T...........................  28R-7703001 through 28R-7803374
                                         and 2803001 through 2803012.
PA-28RT-201...........................  28R-7918001 through 28R-7918267
                                         and 28R-8018001 through 28R-
                                         8218026.
PA-28RT-201T..........................  28R-7931001 through 28R-8631005
                                         and 2831001 through 2831038.
PA-32-260.............................  32-03; 32-04; 32-1 through 32-
                                         1297; and 32-7100001 through 32-
                                         7800008.
PA-32-300.............................  32-15; 32-21; 32-40000 through
                                         32-40974; and 32-7140001
                                         through 32-7940290.
PA-32S-300............................  32S-15; 32S-40000 through 32S-
                                         40974; and 32S-7140001 through
                                         32S-7240137.
PA-32R-300............................  32R-7680001 through 32R-7880068.
PA-32RT-300...........................  32R-7885002 through 32R-7985106.
PA-32RT-300T..........................  32R-7787001 and 32R-7887002
                                         through 32R-7987126.
PA-32R-301 (SP).......................  32R-8013001 through 32R-8613006;
                                         3213001 through 3213028; and
                                         3213030 through 3213041.
PA-32R-301 (HP).......................  3213029; 3213042 through
                                         3213103; 3246001 through
                                         3246217; 3246219; 3246223;
                                         3246218; 3246220 through
                                         3246222; and 3246224 through
                                         3246244.
PA-32R-301T...........................  32R-8029001 through 32R-8629008
                                         and 3229001 through 3229003.
PA-32-301.............................  32-8006002 through 32-8606023;
                                         3206001 through 3206019;
                                         3206042 through 3206044;
                                         3206047; 3206050 through
                                         3206055; and 3206060.
PA-32-301T............................  32-8024001 through 32-8424002.
PA-32R-301T...........................  3257001 through 3257483.
PA-32-301FT...........................  3232001 through 3232074.
PA-32-301XTC..........................  3255001 through 3255014;
                                         3255026, 3255015 through
                                         3255025; 3255027; and 3255051.
PA-34-200.............................  34-E4 and 34-7250001 through 34-
                                         7450220.
PA-34-200T............................  34-7570001 through 34-8170092.
PA-34-220T............................  34-8133001 through 34-8633031;
                                         3433001 through 3433172;
                                         3448001 through 3448037;
                                         3448038 through 3448079;
                                         3447001 through 3447029; and
                                         3449001 through 3449377.
PA-44-180.............................  44-7995001 through 44-8195026;
                                         4495001 through 4495013; and
                                         4496001 through 4496251.
PA-44-180T............................  44-8107001 through 44-8207020.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from two field reports of incorrectly 
assembled control wheel shafts. We are issuing this AD to detect and 
correct any incorrectly assembled control wheel shafts. This 
condition, if left uncorrected, could lead to separation of the 
control wheel shaft, resulting in loss of pitch and roll control.

Compliance

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

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Inspect the pilot and         Within 100 hours    Follow Piper
 copilot control wheel columns     time-in-service     Aircraft, Inc.
 for correct control wheel shaft   (TIS) after the     Mandatory Service
 installation.                     effective date of   Bulletin No.
                                   this AD or within   1197A, dated
                                   60 days after the   September 1,
                                   effective date of   2009.
                                   this AD,
                                   whichever occurs
                                   first.
(2) If during the inspection      Before further      Follow Piper
 required in paragraph (e)(1) of   flight after any    Aircraft, Inc.
 this AD an incorrectly            inspection that     Mandatory Service
 installed control wheel shaft     finds incorrect     Bulletin No.
 is found, replace the             installation of     1197A, dated
 appropriate shaft with a new      the control wheel   September 1,
 shaft.                            shaft.              2009.
(3) Inspect the universal joint   Before further      Follow Piper
 when doing the action required    flight after any    Aircraft, Inc.
 in (e)(2) of this AD, and if      inspection that     Mandatory Service
 any deterioration, excessive      finds incorrect     Bulletin No.
 wear, or damage is found,         installation of     1197A, dated
 replace the universal joint       the control wheel   September 1,
 with a new universal joint.       shaft.              2009.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Atlanta Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
Attn: Hector Hernandez, Aerospace Engineer, Atlanta Aircraft 
Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 
30337; telephone: (404) 474-5587; fax: (404) 474-5606. Before using 
any approved AMOC on any airplane to which the AMOC applies, notify 
your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.

Related Information

    (g) To get copies of the service information referenced in this 
AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, 
Florida 32960; telephone: (772) 567-4361; fax: (772) 978-6573; 
Internet: http://www.newpiper.com/company/publications.asp. To view 
the AD docket, go to U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, or on the Internet at 
http://www.regulations.gov.

    Issued in Kansas City, Missouri, on October 23, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-26200 Filed 10-29-09; 8:45 am]

BILLING CODE 4910-13-P