FR Doc 05-16000

[Federal Register: August 15, 2005 (Volume 70, Number 156)]
[Rules and Regulations]
[Page 47716-47720]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15au05-2]

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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:

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:

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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.
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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.
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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.

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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
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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]]

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Actions Compliance Procedures
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(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.
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(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..
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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]

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