[Federal Register Volume 70, Number 156 (Monday, August 15, 2005)]
[Rules and Regulations]
[Pages 47716-47720]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-16000]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD; 
Amendment 39-14221; AD 2005-17-01]
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: The FAA adopts a new airworthiness directive (AD) for all 
Pilatus Aircraft Ltd. (Pilatus) (also identified as Fairchild Republic 
Company and Fairchild Heli Porter) Model PC-6 airplanes. This AD 
requires

[[Page 47717]]

you to repetitively inspect the stabilizer-trim attachment and 
structural components for cracks, corrosion, and discrepancies and 
replace any defective part with a new part. This AD also requires you 
to replace all Fairchild connecting pieces, part number (P/N) 
6232.0026.XX, with a Pilatus connecting piece and requires you to 
replace fittings without an index after the P/N with an improved part. 
This AD results from mandatory continuing airworthiness information 
(MCAI) issued by the airworthiness authority for Switzerland. We are 
issuing this AD to detect and correct defective stabilizer-trim 
attachments and surrounding structural components, which could result 
in failure of the stabilizer-trim attachment. This failure could lead 
to loss of control of the airplane.

DATES: This AD becomes effective on September 29, 2005.
    As of September 29, 2005, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

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 6580; facsimile: +41 41 619 6576.
    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-2005-20515; Directorate 
Identifier 2005-CE-09-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

    What events have caused this AD? The Federal Office for Civil 
Aviation (FOCA), which is the airworthiness authority for Switzerland, 
recently notified FAA that an unsafe condition may exist on all Pilatus 
Model PC-6 airplanes. The FOCA reports that the lower attachment 
bracket of the horizontal stabilizer actuator broke, which resulted in 
an emergency landing outside the airport.
    The FOCA also reports two other instances of total failure of the 
stabilizer trim attachment on in-service airplanes.
    What is the potential impact if FAA took no action? If not detected 
and corrected, defects in the stabilizer-trim attachment and 
surrounding structural components could cause the stabilizer-trim 
attachment to fail. This failure could lead to loss of control 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 all Pilatus Model PC-6 airplanes. 
This proposal was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on March 24, 2005 (70 FR 15019). The NPRM 
proposed to require you to:

--Inspect the stabilizer-trim attachment and structural components (the 
fitting, the connecting piece, the bearing fork, the bearing support 
assembly, and the auxiliary frame, as applicable) for cracks and 
corrosion;
--Inspect the diameters of the boltholes on the fittings, auxiliary 
frame, and connecting piece (as applicable) for discrepancies;
--Replace any cracked, corroded, or defective part with a new part; and
--Replace all Fairchild connecting pieces with a Pilatus connecting 
piece.

    We received comments on the NPRM requesting the following:

--Incorporate revised service to include a procedure for replacing 
certain fittings with an improved part and to correct the allowable 
limits of the actuator attachment hole diameters;
--Change the repetitive inspection intervals; and
--Clarify the applicability of the affected airplanes.

    As a result of the above comments, we issued a supplemental NPRM 
that was published in the Federal Register on June 14, 2005 (34401). 
The Supplemental NPRM proposed to require you to:

--Inspect the stabilizer-trim attachment and structural components (the 
fitting, the connecting piece, the bearing fork, the bearing support 
assembly, and the auxiliary frame, as applicable) for cracks and 
corrosion;
--Inspect the diameters of the boltholes on the fittings, auxiliary 
frame, and connecting piece (as applicable) for discrepancies;
--Replace any cracked part with a new part;
--Repair or replace corroded or defective part;
--Replace all Fairchild connecting pieces, P/N 6232.0026.XX with a 
Pilatus connecting piece. The Fairchild part has a rivet in the middle 
that is not on the Pilatus part; and
--Replace all fittings, P/N 116.40.06.033 without an index after the P/
N with an improved part, P/N 116.40.06.033 with an index after the P/N 
or P/N 116.40.06.112.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD.
    Pilatus Aircraft Ltd. submitted a comment stating that they have no 
further comments on the Supplemental NPRM.

Comment Issue: Update Reference to the Swiss AD

    What is the commenter's concern? FOCA has superseded Swiss AD HB-
2005-080, effective date March 2, 2005, with Swiss AD HB-2005-263, 
effective date June 16, 2005.
    The commenter requests that the reference to the Swiss AD be 
changed to incorporate the new AD number.
    What is FAA's response to the concern? We concur with the commenter 
and will change the final rule AD action.
    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for the 
changes discussed above and minor editorial corrections. We have 
determined that these changes and 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.

Docket Information

    Where can I go to view the docket information? You may view the AD 
docket that contains information relating to this subject in person at 
the DMS Docket Offices between 9 a.m. and 5 p.m. (eastern standard 
time), Monday through Friday, except Federal holidays. The Docket 
Office (telephone 1-800-647-5227) is located on the plaza level of the 
Department of Transportation NASSIF Building at the street address 
stated in ADDRESSES. You may also view the AD docket on the Internet at 
http://dms.dot.gov.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002),

[[Page 47718]]

which governs the 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.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 41 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 do the 
inspections:

----------------------------------------------------------------------------------------------------------------
                                                          Total cost per
            Labor cost                  Parts cost           airplane          Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
11 work hours x $65 per hour =     Not applicable.....               $715  $715 x 41 = $29,315
 $715.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that will be required based on the results of the inspections. We have 
no way of determining the number of airplanes that may need these 
replacements:

----------------------------------------------------------------------------------------------------------------
                                                                        Total cost per airplane to replace all
               Labor cost                        Parts cost                             parts
----------------------------------------------------------------------------------------------------------------
10 work hours x $65 = $650.............  $2,000 to replace all       $650 + $2,000 = $2,650
                                          parts.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
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

    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 
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-2005-20515; Directorate Identifier 2005-CE-09-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 adding a new AD to read as follows:

2005-17-01 Pilatus Aircraft Ltd.: Amendment 39-14221; Docket No. 
FAA-2005-20515; Directorate Identifier 2005-CE-09-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on September 29, 2005.

What Other ADs Are Affected By This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplanes, all manufacturer 
serial numbers (MSN), that are certificated in any category.

    Note 1: These airplanes are also identified as Fairchild 
Republic Company PC-6 series airplanes and Fairchild Heli Porter PC-
6 series airplanes.


------------------------------------------------------------------------
                                 Models
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(1) PC-6
(2) PC-6-H1
(3) PC-6-H2
(4) PC-6/350
(5) PC-6/350-H1
(6) PC-6/350-H2
(7) PC-6/A
(8) PC-6/A-H1
(9) PC-6/A-H2
(10) PC-6/B-H2
(11) PC-6/B1-H2
(12) PC-6/B2-H2
(13) PC-6/B2-H4
(14) PC-6/C-H2
(15) PC-6/C1-H2
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Switzerland. We are issuing this AD to detect and correct cracks in 
the stabilizer-trim attachment and surrounding structural 
components, which could result in failure of the stabilizer-trim 
attachment. This failure could lead to loss of control of the 
airplane.

What Must I Do To Address This Problem?

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

[[Page 47719]]



------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the following:
(i) the stabilizer-trim       Within the next 100   Follow Pilatus PC-6
 attachment and structural     hours time-in-        Service Bulletin
 components (fitting,          service (TIS) after   No. 53-001, Rev.
 connecting piece, bearing     September 29, 2005    No. 1, dated June
 fork, bearing support         (the effective date   1, 2005.
 assembly, and auxiliary       of this AD).
 frame, as applicable) for     Repetitively
 cracks and corrosion; and.    inspect thereafter
(ii) the diameters of the      at intervals not-to-
 actuator attachment bolt      exceed 3,500 hours
 holes on the fittings,        TIS or 7 years,
 auxiliary frame, and          whichever occurs
 connecting piece (as          first.
 applicable) for
 discrepancies..
-----------------------------
(2) If cracks are found       Replace the           Follow Pilatus PC-6
 during any inspection         defective part        Service Bulletin
 required in paragraph         before further        No. 53-001, Rev.
 (e)(1)(i) of this AD,         flight after the      No. 1, dated June
 replace the defective part    inspection in which   1, 2005.
 with a new part.              cracks are found.
                               After each
                               replacement,
                               continue with the
                               repetitive
                               inspection
                               requirement in
                               paragraph (e)(1) of
                               this AD.
-----------------------------
(3) If corrosion or
 discrepancies are found
 during any inspection
 required in paragraphs
 (e)(1)(i) and (e)(1)(ii) of
 this AD, do the following:
(i) replace the defective     Replace or repair     Follow Pilatus PC-6
 part with a new part if the   the defective part    Service Bulletin
 corrosion or discrepancy is   before further        No. 53-001, Rev.
 beyond the repairable         flight after the      No. 1, dated June
 limits stated in the          inspection in which   1, 2005.
 service information; or.      corrosion or
(ii) repair the defective      discrepancies are
 part if the corrosion or      found. After each
 discrepancy is within the     replacement or
 repairable limits stated in   repair, continue
 the service information..     with the repetitive
                               inspection
                               requirement in
                               paragraph (e)(1) of
                               this AD.
-----------------------------
(4) Replace the following:
(i) all Fairchild connecting  Within the next 100   Follow Pilatus PC-6
 pieces, part number (P/N)     hours TIS after       Service Bulletin
 6232.0026.XX, with a          September 29, 2005    No. 53-001, Rev.
 Pilatus connecting piece, P/  (the effective date   No. 1, dated June
 N 6232.0026.XX. The           of this AD). After    1, 2005.
 Fairchild part has a rivet    replacement,
 in the middle that is not     repetitively
 on the Pilatus part; and.     inspect thereafter
(ii) all fittings, P/N         at intervals not-to-
 116.40.06.033 without an      exceed 3,500 hours
 index after the P/N, with     TIS or 7 years,
 an improved part, P/N         whichever occurs
 116.40.06.033 with an index   first. If after the
 of ``A'' or ``B'' after the   inspection required
 P/N or with P/N               in paragraph (e)(1)
 116.40.06.112..               of this AD, you
                               determine that you
                               already have a P/N
                               116.40.06.033 with
                               an index of ``A''
                               or ``B'' or a P/N
                               116.40.06.112
                               installed,
                               repetitively
                               inspect thereafter
                               at intervals not-to-
                               exceed 3,500 hours
                               TIS or 7 years,
                               whichever occurs
                               first after the
                               part was installed.
-----------------------------
(5) Do not install any of
 the following:
(i) Fairchild connecting      As of September 29,   Follow Pilatus PC-6
 piece, P/N 6232.0026.XX (it   2005 (the effective   Service Bulletin
 has a rivet in the middle     date of this AD).     No. 53-001, Rev.
 that is not on the Pilatus                          No. 1, dated June
 part); and.                                         1, 2005.
(ii) fitting, P/N
 116.40.06.033, without an
 index after the part
 number..
------------------------------------------------------------------------


    Note 2: Even though not required in this AD, the FAA recommends 
that you send all defective parts to Pilatus at the address 
specified in paragraph (h) of this AD. With the part, include the 
aircraft serial number, flying hours, and cycles.

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, Standards Office, Small 
Airplane Directorate, FAA. For information on any already approved 
alternative methods of compliance, 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.

Is There Other Information That Relates to This Subject?

    (g) Swiss AD HB-2005-263, effective date June 16, 2005, also 
addresses the subject of this AD.

Does This AD Incorporate Any Material by Reference?

    (h) You must do the actions required by this AD following the 
instructions in Pilatus PC-6 Service Bulletin No. 53-001, Rev. No. 
1, dated June 1, 2005. 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. To get a copy of 
this service information, contact Pilatus Aircraft Ltd., Customer 
Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 
6580; facsimile: +41 41 619 6576. 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-2005-20515; 
Directorate Identifier 2005-CE-09-AD.


[[Page 47720]]


    Issued in Kansas City, Missouri, on August 8, 2005.
Kim Smith,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-16000 Filed 8-12-05; 8:45 am]
BILLING CODE 4910-13-P