[Federal Register: May 30, 2007 (Volume 72, Number 103)]
[Proposed Rules]
[Page 29895-29897]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30my07-18]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 29895]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28157; Directorate Identifier 2007-CE-046-AD]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
This Airworthiness Directive (AD) is prompted due to the
discovery of cracks in the upper wing strut fittings of some PC-6
aircraft.
It is possible that the spherical bearing of the wing strut
fittings installed in the underwing can be loose in the fitting or
cannot rotate because of corrosion. In this condition, the joint
cannot function as designed and fatigue cracks may then develop.
Undetected cracks in this area could lead to failure of upper
attachment fitting. This could result in the failure of the wing
structure with subsequent loss of control of the airplane.
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by June 29, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
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.
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket 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 AD
docket contains this proposed AD, the regulatory evaluation, any
comments received, and other information. The street address for the
Docket Office (telephone (800) 647-5227) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This proposed AD references the MCAI and related service
information that we considered in forming the engineering basis to
correct the unsafe condition. The proposed AD contains text copied from
the MCAI and for this reason might not follow our plain language
principles.
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28157; Directorate Identifier 2007-CE-046-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because 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 about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No: 2007-0114, dated May 2, 2007 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
This Airworthiness Directive (AD) is prompted due to the
discovery of cracks in the upper wing strut fittings of some PC-6
aircraft.
It is possible that the spherical bearing of the wing strut
fittings installed in the underwing can be loose in the fitting or
cannot rotate because of corrosion. In this condition, the joint
cannot function as designed and fatigue cracks may then develop.
Undetected cracks in this area could lead to failure of upper
attachment fitting. This could result in the failure of the wing
structure with subsequent loss of control of the airplane. In order
to correct and monitor this situation, the present AD mandates a
one-time inspection of the wing strut fittings and replacement of
damaged wing strut fittings with new ones. This AD also requires
examination of the spherical bearings installed in the wing strut
fittings and their replacement for bearings that do not pass the
examination criteria.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Pilatus Aircraft Ltd. has issued Service Bulletin No. 57-004, dated
April 16, 2007. The actions described in this service information are
intended to
[[Page 29896]]
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of the Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed AD and the MCAI or Service
Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 50 products of U.S. registry. We also estimate that
it would take about 7 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $28,000, or $560 per product.
In addition, we estimate that any necessary follow-on actions would
take about 15 work-hours and require parts costing $2,500 for a cost of
$3,700 per fitting or $7,400 per product if both fittings are replaced.
We have no way of determining the number of products that may need
these actions.
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 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 this 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.
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 adding the following new AD:
Pilatus Aircraft Ltd.: Docket No. FAA-2007-28157; Directorate
Identifier 2007-CE-046-AD.
Comments Due Date
(a) We must receive comments by June 29, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to 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; manufacturer serial numbers (MSN) 101 through 951, and
MSN 2001 through 2092; that are certificated in any category. 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.
Subject
(d) Air Transport Association of America (ATA) Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
This Airworthiness Directive (AD) is prompted due to the
discovery of cracks in the upper wing strut fittings of some PC-6
aircraft.
It is possible that the spherical bearing of the wing strut
fittings installed in the underwing can be loose in the fitting or
cannot rotate because of corrosion. In this condition, the joint
cannot function as designed and fatigue cracks may then develop.
Undetected cracks in this area could lead to failure of upper
attachment fitting. This could result in the failure of the wing
structure with subsequent loss of control of the airplane.
In order to correct and monitor this situation, the present AD
mandates a one time inspection of the wing strut fittings and
replacement of damaged wing strut fittings with new ones. This AD
also requires examination of the spherical bearings installed in the
wing strut fittings and their replacement for bearings that do not
pass the examination criteria.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For MSN 2001 through MSN 2092: Within the next 100 hours
time-in-service (TIS) on the upper wing strut fitting after the
effective date of this AD or within 3 months after the effective
date of this AD, whichever occurs first, and repetitively thereafter
at intervals not to exceed 12 months, do the actions specified in
paragraph (f)(3) of this AD.
(2) For MSN 101 through MSN 951 do the following actions, as
applicable:
(i) If the upper wing strut fitting has less than 3,500 hours
TIS or has been installed for less than 84 months (7 years): Within
the next 1,000 hours TIS on the upper wing strut fitting after the
effective date of this AD or within 24 months after the effective
date of this AD without exceeding 3,600 hours TIS
[[Page 29897]]
or 87 months (7 years, 3 months), whichever occurs first, and
repetitively thereafter at intervals not to exceed 12 months, do the
actions specified in paragraph (f)(3) of this AD, or;
(ii) If the upper wing strut fitting has 3,500 or more hours TIS
or has been installed for 84 months (7 years) or longer: Within the
next 100 hours TIS on the upper wing strut fitting after the
effective date of this AD or within 3 months after the effective
date of this AD, whichever occurs first, and repetitively thereafter
at intervals not to exceed 12 months, do the actions specified in
paragraph (f)(3) of this AD.
Note 1: If the TIS of the upper wing strut fittings cannot be
positively determined by a review in the airplane maintenance
records, then by default the upper wing strut fittings were
installed from the date of original Certificate of Airworthiness.
(3) Do the following at the times specified in paragraph (f)(1)
or (f)(2) of this AD:
(i) Perform a visual and non-destructive inspection of the upper
wing strut fittings for cracks following the Accomplishment
Instructions in Pilatus Aircraft Ltd. Service Bulletin No. 57-004,
dated April 16, 2007.
(ii) Examine for conformity the spherical bearings following the
Accomplishment Instructions in Pilatus Aircraft Ltd. Service
Bulletin No. 57-004, dated April 16, 2007.
(4) If during any inspection required by paragraph (f)(3)(i) of
this AD, cracks are found in the upper wing strut fitting, before
further flight replace the wing strut fitting with a new part number
(P/N) 111.35.06.185 (left side) or P/N 111.35.06.186 (right side)
following the Accomplishment Instructions in Pilatus Aircraft Ltd.
Service Bulletin No. 57-004, dated April 16, 2007. Replacement of
the upper wing strut fitting does not terminate the repetitive
inspection specified in paragraph (f)(3) of this AD.
(5) If during any inspection required by paragraph (f)(3)(ii) of
this AD, the spherical bearing is found not in conformity, replace
the bearing with a new P/N 944.61.00.109 following the
Accomplishment Instructions in Pilatus Aircraft Ltd. Service
Bulletin No. 57-004, dated April 16, 2007. Replacement of the
spherical bearing does not terminate the repetitive inspection
specified in paragraph (f)(3) of this AD.
(6) Report to Pilatus Aircraft Ltd. Customer Liaison Manager
results of the inspection/examination using Table 1 of Pilatus
Aircraft Ltd. Service Bulletin No. 57-004, dated April 16, 2007.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows:
(1) The FAA AD is requiring repetitive inspections and reporting
results to the manufacturer, not just a one-time inspection and
report as required in the MCAI.
(2) The Service Bulletin specifies ``subsequent inspections for
cracks will be included in Chapter 5 of the Aircraft Maintenance
Manual (AMM).'' The only way we (FAA) can mandate these repetitive
inspections is through an AD.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Staff, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090. Before using
any approved AMOC on any airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA) AD No:
2007-0114, dated May 02, 2007; and Pilatus Aircraft Ltd. Service
Bulletin No. 57-004, dated April 16, 2007, for related information.
Issued in Kansas City, Missouri, on May 23, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-10315 Filed 5-29-07; 8:45 am]
BILLING CODE 4910-13-P