[Federal Register: June 21, 2006 (Volume 71, Number 119)]
[Rules and Regulations]
[Page 35502-35505]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21jn06-6]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24094; Directorate Identifier 2006-CE-20-AD;
Amendment 39-14656; AD 68-17-03R1]
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).
[[Page 35503]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) to revise
AD 68-17-03, which applies to all Pilatus Aircraft Ltd. (Pilatus) PC-6
series airplanes. AD 68-17-03 requires you to repetitively inspect the
rudder end rib for cracks and replace the rudder end rib with a
modified rudder end rib when you find cracks. Installing the modified
rudder end rib terminates the repetitive inspection requirements of AD
68-17-03. Under a licensing agreement with Pilatus, Fairchild Republic
Company (also identified as Fairchild Industries, Fairchild Heli
Porter, or Fairchild-Hiller Corporation) produced Model PC-6 series
airplanes (manufacturer serial numbers 2001 through 2092) in the United
States. AD 68-17-03 was intended to apply to all affected serial
numbers of Model PC-6 series airplanes listed on Type Certificate Data
Sheet (TCDS) No. 7A15, including the Fairchild-produced airplanes.
Consequently, this AD clarifies that all models of the PC-6 airplane on
TCDS No. 7A15 (including those models produced under the licensing
agreement by Fairchild Republic Company) are included in the
applicability. We are issuing this AD to detect and correct cracks in
the rudder end rib, which could result in failure of the rudder end
rib. This failure could result in loss of rudder control.
DATES: This AD becomes effective on August 3, 2006.
As of August 3, 2006, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
ADDRESSES: For 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 20590-001, or on the Internet at http://dms.dot.gov.
The docket number is FAA-2006-24094; Directorate
Identifier 2006-CE-20-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 April 17, 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 Pilatus PC-6 series airplanes. This proposal was
published in the Federal Register as a notice of proposed rulemaking
(NPRM) on April 24, 2006 (71 FR 20919). The NPRM proposed to revise AD
68-17-03 with a new AD that would retain all actions currently required
by AD 68-17-03 and would clarify the applicability of the affected
airplanes by:
Identifying those airplanes produced in the United States
through a licensing agreement with the Fairchild Republic Company; and
Listing all Pilatus Model PC-6 series airplanes on Type
Certificate Data Sheet No. 7A15 in the applicability section.
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:
----------------------------------------------------------------------------------------------------------------
Total cost for Total cost on U.S.
Labor cost Parts cost each airplane operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $80 an hour = 80........... Not applicable............. $80 $80 x 49 = $3,920
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that will be required based on the results of the inspection. We have
no way of determining the number of airplanes that may need this
replacement:
------------------------------------------------------------------------
Total cost for
Labor cost Parts cost each airplane
------------------------------------------------------------------------
9 work-hours x $80 an hour = $720... $821 $1,541
------------------------------------------------------------------------
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
[[Page 35504]]
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-2006-24094; Directorate Identifier 2006-CE-20-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. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
68-17-03, Amendment 39-634, and adding the following new AD:
68-17-03R1 Pilatus Aircraft LTD.: Amendment 39-14656; Docket No.
FAA-2006-24094; Directorate Identifier 2006-CE-20-AD.
Effective Date
(a) This AD becomes effective on August 3, 2006.
Affected ADs
(b) This AD revises AD 68-17-03, Amendment 39-634.
Applicability
(c) This AD affects the following airplane models, all
manufacturer serial numbers (MSN), that are certificated in any
category:
Note: MSNs 2001 through 2092 were manufactured by Fairchild
Republic Company (also identified as Fairchild Industries, Fairchild
Heli Porter, and Fairchild-Hiller Corporation) in the United States
under a licensing agreement and are covered by Type Certificate Data
Sheet No. 7A15.
(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
Unsafe Condition
(d) This AD results from fatigue cracks found in the bottom nose
rib on the rudders of certain PC-6 airplanes. We are issuing this AD
to detect and correct cracks in the rudder end rib, which could
result in failure of the rudder. This failure could lead to loss of
rudder control.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) With the aid of a mirror, Within the next Follow Pilatus Service
inspect the rudder end rib, 50 hours time- Bulletin No. 80, dated
part number (P/N) 6302.27 in-service April 1968.
(or FAA-approved equivalent after August
P/N) for crack(s). 19, 1968 (the
effective date
of AD 68-17-
03).
Repetitively
inspect
thereafter at
intervals not
to exceed 50
hours TIS.
(2) If you detect a crack or Before further Follow Pilatus Service
cracks during any inspection flight after Bulletin No. 80, dated
required in paragraph (e)(1) any inspection April 1968.
of this AD, replace the required in
rudder end rib with a paragraph
modified rudder end rib (e)(1) of this
assembly, P/N 6302.26 Pos. AD in which you
2, channel reinforcement, P/ find cracks.
N 113.40.06.002, and torque Installing the
tube, P/N 113.40.06.003 (or modified rudder
FAA-approved equivalent P/ end rib
Ns). terminates the
repetitive
inspection
requirement in
paragraph
(e)(1) of this
AD.
(3) 14 CFR 21.303 allows for Not applicable.. Not applicable.
replacement parts through
parts manufacturer approval
(PMA). The phrase ``or FAA-
approved equivalent P/N'' in
this AD is intended to
signify those parts that are
PMA parts 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.
(4) Installing the modified Not applicable.. Not applicable.
rudder end rib assembly, P/N
6302.26 Pos. 2, channel
reinforcement, P/N
113.40.06.002, and torque
tube, P/N 113.40.06.003 (or
FAA-approved equivalent P/
Ns), terminates the
repetitive inspection
requirement in paragraph
(e)(1) of this AD.
------------------------------------------------------------------------
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 68-17-03 are approved for this AD.
Related Information
(h) Swiss AD Number HB 2005-289, effective date August 23, 2005,
also addresses the subject of this AD.
Material Incorporated by Reference
(i) You must do the actions required by this AD following
Pilatus Service Bulletin No. 80, dated April 1968. 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 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
[[Page 35505]]
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-
2006-24094; Directorate Identifier 2006-CE-20-AD.
Issued in Kansas City, Missouri, on June 12, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5532 Filed 6-20-06; 8:45 am]
BILLING CODE 4910-13-P