[Federal Register Volume 71, Number 89 (Tuesday, May 9, 2006)]
[Proposed Rules]
[Pages 26891-26894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-7017]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-6, PC-
6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, 
PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, 
and PC-6/C1-H2 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

[[Page 26892]]

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2003-09-
01, which applies to Pilatus Aircraft Ltd (Pilatus) Model PC-6 
airplanes, all manufacturer serial numbers (MSN) up to and including 
939. AD 2003-09-01 currently requires you to inspect and correct, as 
necessary, the aileron control bellcrank assemblies at the wing and 
fuselage locations. Since we issued AD 2003-09-01, the FAA determined 
the action should also apply to all the models of the PC-6 airplanes 
listed in the type certification data sheet of Type Certificate (TC) 
No. 7A15 that are produced in the United States through a licensing 
agreement between Pilatus and Fairchild Republic Company (also 
identified as Fairchild Industries, Fairchild Heli Porter, or 
Fairchild-Hiller Corporation). In addition, the intent of the 
applicability of AD 2003-09-01 was to all the affected serial numbers 
of the airplane models listed in TC No. 7A15. Consequently, this 
proposed AD would retain all the actions of AD 2003-09-01, would add 
those Fairchild Republic Company airplanes to the applicability of this 
proposed AD, and would list out the individual specific airplane 
models. We are proposing this AD to detect and correct increased 
friction in the aileron control bellcrank assemblies, which could 
result in failure of the aileron flight-control system. Such failure 
could lead to problems in controlling flight.

DATES: We must receive comments on this proposed AD by June 9, 2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     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.
    For service information identified in this proposed AD, contact 
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224.

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

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-
2006-24092; Directorate Identifier 2006-CE-18-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://dms.dot.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

    Mandatory continuing airworthiness information and the FAA's 
determination that an unsafe condition existed on a Pilatus Model PC-6 
airplane caused us to issue AD 2003-09-01, Amendment 39-13130 (68 FR 
22582, April 29, 2003). AD 2003-09-01 currently requires you to inspect 
and correct, as necessary, the aileron control bellcrank assemblies at 
the wing and fuselage locations on Pilatus Model PC-6 airplanes.
    The Federal Office for Civil Aviation (FOCA), which is the 
airworthiness authority for Switzerland, notified the FAA of the need 
to supersede AD 2003-09-01 to address an unsafe condition that may 
exist or could develop on Model PC-6 airplanes, all manufacturer serial 
numbers (MSN) up to and including 939. The FOCA reports that the AD 
action should also apply to all the models of the PC-6 airplanes listed 
in the type certification data sheet of TC No. 7A15 produced in the 
United States through a licensing agreement between Pilatus and 
Fairchild Republic Company (also identified as Fairchild Industries, 
Fairchild Heli Porter, or Fairchild-Hiller Corporation).
    This condition, if not corrected, could result in increased 
friction in the aileron control bellcrank assemblies, which could 
result in failure of the aileron flight-control system. Such failure 
could lead to problems in controlling flight.

Foreign Airworthiness Authority Information

    The FOCA recently issued Swiss AD Number HB 2005-289, effective 
date August 23, 2005, to ensure the continued airworthiness of all 
models of the PC-6 airplanes listed in TC No. 7A15, including those 
produced in the United States under a licensing agreement with Pilatus 
and Fairchild Republic Company (also identified as Fairchild 
Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation).
    The State of Design for the Pilatus PC-6 airplanes is Switzerland 
and the airplanes are type-certificated for operation in the United 
States under the provisions of section 21.29 of the Federal Aviation 
Regulations (14 CFR 21.29) and the applicable bilateral airworthiness 
agreement.
    Under this bilateral airworthiness agreement, the FOCA has kept us 
informed of the situation described above.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we have examined the FOCA's 
findings, evaluated all information and determined the unsafe condition 
described previously is likely to exist or develop on other products of 
the same type design that are certificated for operation in the United 
States.
    This proposed AD would supersede AD 2003-09-01 with a new AD that 
would retain all the actions of AD 2003-09-01 and would:
     Add manufacturer serial numbers (MSN) 2001 through 2092 
for all the models of the PC-6 airplanes as listed in TC No. 7A15 and 
specified in the applicability section. These MSN are the airplanes 
produced in the United States through a licensing agreement with the 
Fairchild Republic Company; and
     List all the models of the PC-6 airplanes as listed in TC 
No. 7A15.

Costs of Compliance

    We estimate that this proposed AD would affect 49 airplanes in the 
U.S. registry.
    We estimate the following costs to do the proposed inspection and 
modifications:

[[Page 26893]]



----------------------------------------------------------------------------------------------------------------
                                                          Total cost
                Labor cost                  Parts cost   per airplane        Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
7 work hours x $80 per hour = $560.......         $300          $860   $860 x 49 = $42,140.
----------------------------------------------------------------------------------------------------------------

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://dms.dot.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) 647-5227) 
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, 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 removing Airworthiness Directive 
(AD) 2003-09-01, Amendment 39-13130, and adding the following new AD:

Pilatus Aircraft LTD.: Docket No. FAA-2006-24092; Directorate 
Identifier 2006-CE-18-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by June 9, 2006.

Affected ADs

    (b) This AD supersedes AD 2003-09-01, Amendment 39-13130.

Applicability

    (c) This AD affects the following Models PC-6, PC-6-H1, PC-6-H2, 
PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, 
PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/
C1-H2 airplanes that are equipped with turbo-prop engines and are 
certificated in any category:
    (1) Group 1 (maintains the actions from AD 2003-09-01): All 
manufacturer serial numbers (MSN) up to and including 939.
    (2) Group 2: MSN 2001 through 2092.

    Note: These airplanes are also identified as Fairchild Republic 
Company PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or 
Fairchild-Hiller Corporation PC-6 airplanes.

Unsafe Condition

    (d) This AD results from mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Switzerland that requires retaining the actions of AD 2003-09-01 and 
adding MSN 2001 through 2092 for all the models of the PC-6 
airplanes listed in the type certificate data sheet of Type 
Certificate (TC) No. 7A15. We are issuing this AD to detect and 
correct increased friction in the aileron control bellcrank 
assemblies, which could result in failure of the aileron flight-
control system. Such failure could lead to problems in controlling 
flight.

Compliance

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

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect, before removal   (A) For Group 1       Follow Pilatus
 of the wing bellcrank         Airplanes: Within     Aircraft Ltd. PC-6
 assemblies, part numbers (P/  the next 100 hours    Service Bulletin
 N) 6132.0071.51 and           time-in-service       No. 27-001, dated
 6132.0071.52, for installed   (TIS) after June      June 5, 2002.
 circlips, P/N N237:           17, 2003 (the
(i) If circlips are            effective date of
 installed, do the actions     AD 2003-09-01),
 required in paragraphs        unless already done.
 (e)(5) and (e)(6) of this    (B) For Group 2
 AD.                           Airplanes: Within
(ii) If circlips are not       the next 100 hours
 installed, perform all        TIS after the
 actions required by           effective date of
 paragraphs (e)(3), (e)(4),    this AD, unless
 (e)(5), (e)(6), and (e)(7)    already done.
 of this AD.

[[Page 26894]]

 
(2) Inspect, before removal   Before further        Follow Pilatus
 of the fuselage bellcrank     flight after the      Aircraft Ltd. PC-6
 assembly, P/N 6232.0118.00,   inspection required   Service Bulletin
 for the circlip installed     in paragraph (e)(1)   No. 27-001, dated
 on the housing to prevent     of this AD.           June 5, 2002.
 axial movement of the
 bellcrank on its bearing
 and the flange of the
 housing to the rear. If the
 fuselage bellcrank assembly
 has either no circlip and/
 or it is not installed as
 required, perform the
 actions in paragraphs
 (e)(8) and (e)(9) of this
 AD.
(3) Remove the wing           Before further        Follow Pilatus
 bellcrank assemblies, P/Ns    flight after the      Aircraft Ltd. PC-6
 6132.0071.51 and              inspections           Service Bulletin
 6132.0071.52, and inspect     required in           No. 27-001, dated
 for worn or damaged           paragraphs (e)(1)     June 5, 2002.
 bearings. Replace worn or     and (e)(2) of this
 damaged bearings.             AD, as applicable.
(4) Stake and lock the        Before further        Follow Pilatus
 bearing in the housing of     flight after the      Aircraft Ltd. PC-6
 the wing bellcranks, P/Ns     inspections           Service Bulletin
 6132.0071.51 and              required in           No. 27-001, dated
 6132.0071.52.                 paragraphs (e)(1)     June 5, 2002.
                               and (e)(2) of this
                               AD, as applicable.
(5) Inspect the wing          Before further        Follow Pilatus
 bellcranks control-cable      flight after the      Aircraft Ltd. PC-6
 attachment bolts for          inspections           Service Bulletin
 correct type and for signs    required in           No. 27-001, dated
 of rub damage on the heads.   paragraphs (e)(1)     June 5, 2002.
 Replace bolts that are        and (e)(2) of this
 damaged and/or have a total   AD.
 length (including head) of
 more than 21.5 mm (0.85
 in.)
(6) Inspect the wing          Before further        Follow Pilatus
 bellcranks support plate      flight after the      Aircraft Ltd. PC-6
 for signs of rub damage       inspections           Service Bulletin
 caused by the bolts. If       required in           No. 27-001, dated
 damage is found:              paragraphs (e)(1)     June 5, 2002.
(i) Obtain a repair scheme     and (e)(2) of this
 from the manufacturer         AD.
 through FAA at the address
 specified in paragraph (f)
 of this AD.
(ii) Incorporate this repair
 scheme..
(7) Reinstall wing bellcrank  Before further        Follow Pilatus
 assemblies.                   flight after the      Aircraft Ltd. PC-6
                               inspections           Service Bulletin
                               required in           No. 27-001, dated
                               paragraphs (e)(1)     June 5, 2002.
                               and (e)(2) of this
                               AD.
(8) Remove the fuselage       Before further        Follow Pilatus
 bellcrank assembly, P/N       flight after the      Aircraft Ltd. PC-6
 6232.0118.00, and inspect     inspections           Service Bulletin
 the housing for wear,         required in           No. 27-001, dated
 damage, and signs of axial    paragraphs (e)(1)     June 5, 2002.
 movement of the bearing in    and (e)(2) of this
 the housing. Replace worn     AD.
 or damaged bearings. If any
 signs of axial movement of
 a bearing are found:
(i) Obtain a repair scheme
 from the manufacturer
 through FAA at the address
 specified in paragraph (f)
 of this AD.
(ii) Incorporate this repair
 scheme..
(9) Reinstall the fuselage    Before further        Follow Pilatus
 bellcrank assembly. Ensure    flight after the      Aircraft Ltd. PC-6
 that the fuselage bellcrank   inspections           Service Bulletin
 assembly is installed so      required in           No. 27-001, dated
 that the surface of the       paragraphs (e)(1),    June 5, 2002.
 bellcrank with the flange     (e)(2) and (e)(8)
 of the housing is installed   of this AD.
 to the rear. The effect of
 this is to lock the
 bellcrank on the bearing
 tube and thus prevent
 movement.
(10) Do not install any       (A) For Group 1       Follow Pilatus
 bellcrank assemblies, P/Ns    Airplanes: As of      Aircraft Ltd. PC-6
 6132.0071.51, 6132,0071.52,   June 17, 2003 (the    Service Bulletin
 and 6232.0118.00 (or FAA-     effective date of     No. 27-001, dated
 approved equivalent part      AD 2003-09-01).       June 5, 2002.
 numbers), unless the         (B) For Group 2
 aileron assembly has been     Airplanes: As of
 inspected, modified, and      the effective date
 installed.                    of this AD.
------------------------------------------------------------------------


    Note 1: Axial movement of serviceable bearings in the housings 
of the wing bellcranks is permitted provided no wear or damage to 
the bearing is found.


    Note 2: Any signs of axial movement of a bearing in the housing 
of the fuselage bellcrank assembly requires that you obtain a repair 
scheme from the manufacturer through FAA at the address specified in 
paragraph (f) of this AD and incorporate the repair scheme.

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Standards Office, ATTN: Doug Rudolph, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.
    (g) AMOCs approved for AD 2003-09-01 are approved for this AD.

Related Information

    (h) To get copies of the documents referenced in this AD, 
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 
Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 
619 6224. 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, or on the 
Internet at http://dms.dot.gov. The docket number is Docket No. FAA-
2006-24092; Directorate Identifier 2006-CE-18-AD.

    Issued in Kansas City, Missouri, on May 3, 2006.
Barry R. Ballenger,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-7017 Filed 5-8-06; 8:45 am]
BILLING CODE 4910-13-P