[Federal Register Volume 71, Number 138 (Wednesday, July 19, 2006)]
[Rules and Regulations]
[Pages 40888-40891]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-11333]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24092; Directorate Identifier 2006-CE-18-AD; 
Amendment 39-14682; AD 2006-15-02]
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), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) that 
supersedes AD 2003-09-01, which applies to certain Pilatus Aircraft Ltd 
(Pilatus) Model PC-6 airplanes. 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 certificate data sheet 
of Type Certificate (TC) No. 7A15 that were 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 apply to all the affected 
serial numbers of the airplane models listed in TC No. 7A15. This AD 
retains all the actions of AD 2003-09-01, adds those Fairchild Republic 
Company airplanes to the applicability of this AD, and lists the 
individual specific airplane models. 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.

DATES: This AD becomes effective on August 23, 2006.
    As of June 17, 2003 (68 FR 22582, April 29, 2003), the Director of 
the Federal Register previously approved the incorporation by reference 
of Pilatus Service Bulletin No. 27-001, dated June 5, 2002, in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

ADDRESSES: To get the service information identified 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 20590-

[[Page 40889]]

001 or on the Internet at http://dms.dot.gov. The docket number is FAA-
2006-24092; Directorate Identifier 2006-CE-18-AD.

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:

Discussion

    On May 3, 2006, 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 the models of the PC-6 airplanes listed in the type 
certificate data sheet of TC No. 7A15 that were 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) airplanes. This proposal 
was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on May 9, 2006 (71 FR 26891). The NPRM proposed to 
supersede AD 2003-09-01 (68 FR 22582, April 29, 2003), add those 
Fairchild Republic Company airplanes to the applicability of this 
proposed AD, and would list the individual specific airplane models. 
The NPRM proposed to retain all of the actions of AD 2003-09-01 for 
inspecting and correcting, as necessary, the aileron control bellcrank 
assemblies at the wing and fuselage locations.

Comments

    We provided the public the opportunity to participate in developing 
this AD. We received one comment in favor of the proposed AD.

Conclusion

    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.

Costs of Compliance

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

----------------------------------------------------------------------------------------------------------------
                                                        Total cost per
             Labor cost                  Parts cost        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 AD.

Regulatory Findings

    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.
    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 
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-2006-24092; Directorate Identifier 2006-CE-18-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. FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2003-09-01, Amendment 39-13130 (68 FR 22582, April 29, 2003), and by 
adding the following new AD:

2006-15-02 Pilatus Aircraft Ltd.: Amendment 39-14682; Docket No. 
FAA-2006-24092; Directorate Identifier 2006-CE-18-AD.

Effective Date

    (a) This AD becomes effective on August 23, 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 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 Industries 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

[[Page 40890]]

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 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 August
 actions required by           23, 2006 (the
 paragraphs (e)(3), (e)(4),    effective date of
 (e)(5), (e)(6), and (e)(7)    this AD), unless
 of this AD.                   already done.
(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, as applicable.
 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      August 23, 2006
 installed.                    (the effective date
                               of this AD), unless
                               already done.
------------------------------------------------------------------------


[[Page 40891]]

    (f) Axial movement of serviceable bearings in the housings of 
the wing bellcranks is permitted provided no wear or damage to the 
bearing is found.
    (g) Any sign 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 (i) of this AD and incorporate the repair scheme.
    (h) 14 CFR 21.303 allows for replacement parts through parts 
manufacturer approval (PMA). The phrase ``or FAA-approved equivalent 
part number'' in this AD is intended to signify those parts that are 
PMA approved through identicality to the design of the part under 
the type certificate and replacement parts to correct the unsafe 
condition under PMA (other than identicality). If parts are 
installed that are identical to the unsafe parts, then the 
corrective actions of the AD affect these parts also. In addition, 
equivalent replacement parts to correct the unsafe condition under 
PMA (other than identicality) may also be installed provided they 
meet current airworthiness standards, which include those actions 
cited in this AD.

Alternative Methods of Compliance (AMOCs)

    (i) 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.
    (j) AMOCs approved for AD 2003-09-01 are approved for this AD.

Related Information

    (k) Swiss AD Number HB 2005-289, effective date August 23, 2005, 
also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must do the actions required by this AD following the 
instructions in Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 27-
001, dated June 5, 2002.
    (1) As of June 17, 2003 (68 FR 22582, April 29, 2003), the 
Director of the Federal Register previously approved the 
incorporation by reference of Pilatus Service Bulletin No. 27-001, 
dated June 5, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) To get a copy of this service information, contact Pilatus 
Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; 
telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. 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-2006-
24092; Directorate Identifier 2006-CE-18-AD.

    Issued in Kansas City, Missouri, on July 10, 2006.
Steven W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-11333 Filed 7-18-06; 8:45 am]
BILLING CODE 4910-13-P