Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes, 35843-35845 [E6-9845]

Download as PDF Federal Register / Vol. 71, No. 120 / Thursday, June 22, 2006 / Proposed Rules has an illegible CAGE code or Code 15716 or 26098 with an FAA approved airworthy slider without a CAGE code or with a legible CAGE code other than 15716 or 26098. Any T/R slider removed from service based on the requirements of this paragraph is not eligible for installation on any helicopter. (iv) Replacing the T/R slider with an FAA approved airworthy T/R slider without a CAGE code or with a legible CAGE code other than 15716 or 26098, constitutes terminating action for the requirements of this AD. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Denver Aircraft Certification Office (ANM–100D), ATTN: Kreg Voorhies, Aerospace Engineer, 26805 E. 68th Ave., Room 214, Denver, Colorado 80249, telephone (303) 342–1092, fax (303) 342–1088, for information about previously approved alternative methods of compliance. Issued in Fort Worth, Texas, on June 15, 2006. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06–5600 Filed 6–21–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2004–SW–16–AD] RIN 2120–AA64 Airworthiness Directives; MD Helicopters, Inc., Model 600N Helicopters Federal Aviation Administration, DOT. ACTION: Proposed rule; withdrawal. AGENCY: The FAA withdraws a notice of proposed rulemaking (NPRM) proposing a new Airworthiness Directive (AD) for MD Helicopters, Inc. (MDHI) Model 600N helicopters. The NPRM proposed adding six more inspection holes in the aft fuselage skin panels and inspecting the upper and lower tailboom attachment fittings, the upper longerons, and the angles and nutplates for cracks. Also, the NPRM proposed a terminating action of modifying the fuselage aft section to strengthen the tailboom attachments and longerons. Since issuing the NPRM, we have received a report of an in-flight separation of the tailboom in the inspection area. Based on that accident and due to the critical unsafe condition, we issued a final rule; request for comments that addressed the actions mstockstill on PROD1PC68 with PROPOSALS SUMMARY: VerDate Aug<31>2005 18:02 Jun 21, 2006 Jkt 208001 proposed in the NPRM. Accordingly, we withdraw the proposed AD. ADDRESSES: This information may be examined at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas. FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5322, fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Discussion A proposal to amend 14 CFR part 39 by superseding AD 2001–24–51, Docket 2001–SW–57–AD, Amendment 39– 12706 (67 FR 17934, April 12, 2002), for the MDHI Model 600N helicopters was published in the Federal Register on February 10, 2005 (70 FR 7063). In addition to retaining various requirements of AD 2001–24–51, the action proposed installing six more inspection holes in the aft fuselage skin panels and inspecting the upper and lower tailboom attachment fittings, the upper longerons, and the angles and nutplates for cracks. Also, the action proposed a terminating action of modifying the fuselage aft section to strengthen the tailboom attachments and longerons. That actions was prompted by analysis that shows that certain tailboom attachments and longerons may develop cracks. The proposed actions were intended to prevent failure of a tailboom attachment, loss of the tailboom, and subsequent loss of control of the helicopter. Since issuing the NPRM, we have received an additional report of an inflight separation of the tailboom in the inspection area. After reviewing the data, we issued a final rule; request for comments (AD 2006–08–12, 71 FR 24808, April 27, 2006) to correct a critical unsafe condition. That AD, 2006–08–12, requires the necessary actions proposed in the NPRM as well as other actions necessary to correct the unsafe condition. FAA’s Conclusion Since we issued AD 2006–08–12, which includes the necessary actions that were previously proposed, we are withdrawing the NPRM. Withdrawal of the NPRM does not preclude the FAA from issuing another notice in the future nor does it commit the agency to any course of action in the future. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 35843 Regulatory Impact Since this action only withdraws an NPRM, it is neither a proposed nor a final rule and therefore is not covered under Executive Order 12866, the Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Withdrawal Accordingly, we withdraw the NPRM, Docket No. 2004–SW–16–AD, published in the Federal Register on February 10, 2005, 70 FR 7063, FR Doc. 05–2608, filed February 9, 2005. Issued in Fort Worth, Texas, on June 9, 2006. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E6–9846 Filed 6–21–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24954; Directorate Identifier 2006–CE–30–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Models PC–12 and PC–12/ 45 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: Notice of proposed rulemaking (NPRM). ACTION: 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) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The proposed AD would require actions that are intended to address an unsafe condition described in the MCAI. We must receive comments on this proposed AD by July 24, 2006. DATES: E:\FR\FM\22JNP1.SGM 22JNP1 35844 Federal Register / Vol. 71, No. 120 / Thursday, June 22, 2006 / Proposed Rules Use one of the following addresses to comment on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • 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. For service information identified in the proposed AD, contact the Pilatus Aircraft Ltd., Customer Support Manager, CH–6371 STANS, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; email: SupportPC12@pilatusaircraft.com. ADDRESSES: 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: mstockstill on PROD1PC68 with PROPOSALS Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. We are prototyping this process and specifically request your comments on its use. You can find more information in FAA draft Order 8040.2, ‘‘Airworthiness Directive Process for Mandatory Continuing Airworthiness Information’’ which is currently open for comments at https:// www.faa.gov/aircraft/draft_docs. 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 existing AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to follow our technical decision-making processes in all aspects to meet our responsibilities to determine 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 VerDate Aug<31>2005 15:29 Jun 21, 2006 Jkt 208001 text copied from the MCAI and for this reason might not follow our plain language principles. The comment period for this proposed AD is open for 30 days to allow time for comment on both the process and the AD content. In the future, ADs using this process will have a 15-day comment period. The comment period is reduced because the airworthiness authority and manufacturer have already published the documents on which we based our decision, making a longer comment period unnecessary. Comments Invited We invite you to send any written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2006–24954; Directorate Identifier 2006–CE–30–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We are also inviting comments, views, or arguments on the new MCAI process. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this proposed AD. Discussion The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, has issued FOCA AD HB–2006–223, effective date April 20, 2006 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states that the aircraft manufacturer has identified drill damage on some Frame 21 (FR21) lug fittings on the production line and during a number of midlife wing lug inspections. It is thought that the damage found on the FR21 lug fittings occurred during assembly of the airplane. Depending on the size and location of the possible damage, if not corrected, the fatigue life of the wing attachment lugs on FR21 may be affected. The MCAI requires a one-time inspection of the FR21 adjacent to the wing upper-attachment lugs, left and right, and a repair if necessary. You may obtain further information by examining the MCAI in the docket. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Relevant Service Information Pilatus Aircraft Ltd. issued Service Bulletin No. 53–004, dated February 10, 2006. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product is manufactured outside the United States and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral agreement. Pursuant to this bilateral airworthiness agreement, the State of Design’s airworthiness authority has notified us of the unsafe condition described in the MCAI and service information referenced above. We have examined the airworthiness authority’s findings, evaluated all pertinent information, and determined an unsafe condition exists and is likely to exist or develop on all products of this type design. We are issuing this proposed AD to correct the unsafe condition. Differences Between the 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 a U.S. court of law. 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 described in a separate paragraph of the proposed AD. These proposed requirements, if ultimately adopted, will take precedence over the actions copied from the MCAI. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 394 products of U.S. registry. We also estimate that it would take about 5 work-hours per product to do the action and that the average labor rate is $80 per work-hour. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the E:\FR\FM\22JNP1.SGM 22JNP1 Federal Register / Vol. 71, No. 120 / Thursday, June 22, 2006 / Proposed Rules proposed AD on U.S. operators to be $157,600, or $400 per product. Authority for This Rulemaking Title 49 of the United States Code specifies 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 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. mstockstill on PROD1PC68 with PROPOSALS Regulatory Findings We have 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 that the 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. Examining the AD Docket You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments received, and other information on the Internet at https://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 Docket Office (telephone (800) 647–5227) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. VerDate Aug<31>2005 15:29 Jun 21, 2006 Jkt 208001 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 Federal Aviation Administration 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Pilatus Aircraft Ltd.: FAA–2006–24954; Directorate Identifier 2006–CE–30–AD. Comments Due Date (a) We must receive comments on this proposed airworthiness directive (AD) by July 24, 2006. Affected ADs (b) None. Reason (d) The mandatory continuing airworthiness information (MCAI) states that the aircraft manufacturer has identified drill damage on some Frame 21 (FR21) lug fittings on the production line and during a number of midlife wing lug inspections. It is thought that the damage found on the FR21 lug fittings occurred during assembly of the airplane. Depending on the size and location of the possible damage, if not corrected, the fatigue life of the wing attachment lugs on FR21 may be affected. The MCAI requires a one-time inspection of the FR21 adjacent to the wing upper-attachment lugs, left and right, and a repair if necessary. Actions and Compliance (e) Unless already done, do the following except as stated in paragraph (f) below. (1) Within the next 100 hours time-inservice (TIS) after the effective date of this AD, perform an inspection of FR21 in the area of the outer sidewall frame attachment lug forward and aft side faces, left and right, to determine if there is any damage that may have been made with a drill. Follow Pilatus Aircraft Ltd. Service Bulletin No. 53–004, dated February 10, 2006. (2) Within the next 100 hours TIS after the effective date of this AD, perform an inspection of FR21 in the area of the top surface of the wing upper-attachment lugs, left and right, to determine if there is any damage that may have been made with a drill. Follow Pilatus Aircraft Ltd. Service Frm 00010 Bulletin No. 53–004, dated February 10, 2006. (3) If during the inspection required by paragraph (e)(1) of this AD any damage less than 0.1 mm (0.0040 inch) on any FR21 is found, prior to further flight, repair the damaged FR21 in accordance with Pilatus Aircraft Ltd. Service Bulletin No. 53–004, dated February 10, 2006. (4) If during the inspection required in paragraph (e)(1) of this AD any damage equal to or greater than 0.1 mm (0.0040 inch) on any FR21 is found, prior to further flight contact Pilatus Aircraft Ltd. for an FAAapproved repair solution. (5) If during the inspection required by paragraph (e)(2) of this AD any damage less than 1 mm (0.040 inch) depth on any FR21 wing attachment lug top surface is found, prior to further flight, repair the damaged FR21 in accordance with Pilatus Aircraft Ltd. Service Bulletin No. 53–004, dated February 10, 2006. (6) If during the inspection required by paragraph (e)(2) of this AD any damage equal to or greater than 1 mm (0.040 inch) depth on any FR21 wing attachment lug top surface is found, prior to further flight contact Pilatus Aircraft Ltd. for an FAA-approved repair solution. FAA AD Differences Applicability (c) This AD applies to Models PC–12 and PC–12/45 airplanes; manufacturer serial numbers 101 through 617 inclusive, certificated in any U.S. category. PO 00000 35845 Fmt 4702 Sfmt 4702 (f) None. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, 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. (2) Return to Airworthiness: When complying with this AD, perform FAAapproved corrective actions before returning the product to an airworthy condition. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) This AD is related to Federal Office for Civil Aviation AD HB–2006–223, effective date April 20, 2006, which references Pilatus Aircraft Ltd. Service Bulletin No. 53–004, dated February 10, 2006. Issued in Kansas City, Missouri, on June 12, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–9845 Filed 6–21–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\22JNP1.SGM 22JNP1

Agencies

[Federal Register Volume 71, Number 120 (Thursday, June 22, 2006)]
[Proposed Rules]
[Pages 35843-35845]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9845]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24954; Directorate Identifier 2006-CE-30-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and 
PC-12/45 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

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) issued by an airworthiness 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The proposed AD would require actions 
that are intended to address an unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by July 24, 2006.

[[Page 35844]]


ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     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.
    For service information identified in the proposed AD, contact the 
Pilatus Aircraft Ltd., Customer Support Manager, CH-6371 STANS, 
Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-
mail: SupportPC12@pilatus-aircraft.com.

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:

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. We are prototyping this process and 
specifically request your comments on its use. You can find more 
information in FAA draft Order 8040.2, ``Airworthiness Directive 
Process for Mandatory Continuing Airworthiness Information'' which is 
currently open for comments at https://www.faa.gov/aircraft/draft_docs. 
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 existing AD issuance processes 
to meet legal, economic, Administrative Procedure Act, and Federal 
Register requirements. We also continue to follow our technical 
decision-making processes in all aspects to meet our responsibilities 
to determine 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.
    The comment period for this proposed AD is open for 30 days to 
allow time for comment on both the process and the AD content. In the 
future, ADs using this process will have a 15-day comment period. The 
comment period is reduced because the airworthiness authority and 
manufacturer have already published the documents on which we based our 
decision, making a longer comment period unnecessary.

Comments Invited

    We invite you to send any written data, views, or arguments 
regarding this proposed AD. Send your comments to an address listed 
under the ADDRESSES section. Include the docket number, ``FAA-2006-
24954; Directorate Identifier 2006-CE-30-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We are 
also inviting comments, views, or arguments on the new MCAI process. We 
will consider all comments received by the closing date and may amend 
the proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    The Federal Office for Civil Aviation (FOCA), which is the 
airworthiness authority for Switzerland, has issued FOCA AD HB-2006-
223, effective date April 20, 2006 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states that the aircraft manufacturer has identified drill damage 
on some Frame 21 (FR21) lug fittings on the production line and during 
a number of midlife wing lug inspections. It is thought that the damage 
found on the FR21 lug fittings occurred during assembly of the 
airplane. Depending on the size and location of the possible damage, if 
not corrected, the fatigue life of the wing attachment lugs on FR21 may 
be affected. The MCAI requires a one-time inspection of the FR21 
adjacent to the wing upper-attachment lugs, left and right, and a 
repair if necessary. You may obtain further information by examining 
the MCAI in the docket.

Relevant Service Information

    Pilatus Aircraft Ltd. issued Service Bulletin No. 53-004, dated 
February 10, 2006. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product is manufactured outside the United States and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral agreement. Pursuant to this bilateral 
airworthiness agreement, the State of Design's airworthiness authority 
has notified us of the unsafe condition described in the MCAI and 
service information referenced above. We have examined the 
airworthiness authority's findings, evaluated all pertinent 
information, and determined an unsafe condition exists and is likely to 
exist or develop on all products of this type design. We are issuing 
this proposed AD to correct the unsafe condition.

Differences Between the 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 a U.S. court of 
law. 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 
described in a separate paragraph of the proposed AD. These proposed 
requirements, if ultimately adopted, will take precedence over the 
actions copied from the MCAI.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 394 products of U.S. registry. We also estimate that 
it would take about 5 work-hours per product to do the action and that 
the average labor rate is $80 per work-hour. Where the service 
information lists required parts costs that are covered under warranty, 
we have assumed that there will be no charge for these costs. As we do 
not control warranty coverage for affected parties, some parties may 
incur costs higher than estimated here. Based on these figures, we 
estimate the cost of the

[[Page 35845]]

proposed AD on U.S. operators to be $157,600, or $400 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies 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 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 have 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 that the 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.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at https://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 Docket Office (telephone (800) 647-5227) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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 Federal Aviation Administration 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.: FAA-2006-24954; Directorate Identifier 2006-
CE-30-AD.

Comments Due Date

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by July 24, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Models PC-12 and PC-12/45 airplanes; 
manufacturer serial numbers 101 through 617 inclusive, certificated 
in any U.S. category.

Reason

    (d) The mandatory continuing airworthiness information (MCAI) 
states that the aircraft manufacturer has identified drill damage on 
some Frame 21 (FR21) lug fittings on the production line and during 
a number of midlife wing lug inspections. It is thought that the 
damage found on the FR21 lug fittings occurred during assembly of 
the airplane. Depending on the size and location of the possible 
damage, if not corrected, the fatigue life of the wing attachment 
lugs on FR21 may be affected. The MCAI requires a one-time 
inspection of the FR21 adjacent to the wing upper-attachment lugs, 
left and right, and a repair if necessary.

Actions and Compliance

    (e) Unless already done, do the following except as stated in 
paragraph (f) below.
    (1) Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD, perform an inspection of FR21 in the area 
of the outer sidewall frame attachment lug forward and aft side 
faces, left and right, to determine if there is any damage that may 
have been made with a drill. Follow Pilatus Aircraft Ltd. Service 
Bulletin No. 53-004, dated February 10, 2006.
    (2) Within the next 100 hours TIS after the effective date of 
this AD, perform an inspection of FR21 in the area of the top 
surface of the wing upper-attachment lugs, left and right, to 
determine if there is any damage that may have been made with a 
drill. Follow Pilatus Aircraft Ltd. Service Bulletin No. 53-004, 
dated February 10, 2006.
    (3) If during the inspection required by paragraph (e)(1) of 
this AD any damage less than 0.1 mm (0.0040 inch) on any FR21 is 
found, prior to further flight, repair the damaged FR21 in 
accordance with Pilatus Aircraft Ltd. Service Bulletin No. 53-004, 
dated February 10, 2006.
    (4) If during the inspection required in paragraph (e)(1) of 
this AD any damage equal to or greater than 0.1 mm (0.0040 inch) on 
any FR21 is found, prior to further flight contact Pilatus Aircraft 
Ltd. for an FAA-approved repair solution.
    (5) If during the inspection required by paragraph (e)(2) of 
this AD any damage less than 1 mm (0.040 inch) depth on any FR21 
wing attachment lug top surface is found, prior to further flight, 
repair the damaged FR21 in accordance with Pilatus Aircraft Ltd. 
Service Bulletin No. 53-004, dated February 10, 2006.
    (6) If during the inspection required by paragraph (e)(2) of 
this AD any damage equal to or greater than 1 mm (0.040 inch) depth 
on any FR21 wing attachment lug top surface is found, prior to 
further flight contact Pilatus Aircraft Ltd. for an FAA-approved 
repair solution.

FAA AD Differences

    (f) None.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Staff, FAA, 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.
    (2) Return to Airworthiness: When complying with this AD, 
perform FAA-approved corrective actions before returning the product 
to an airworthy condition.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) This AD is related to Federal Office for Civil Aviation AD 
HB-2006-223, effective date April 20, 2006, which references Pilatus 
Aircraft Ltd. Service Bulletin No. 53-004, dated February 10, 2006.

    Issued in Kansas City, Missouri, on June 12, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-9845 Filed 6-21-06; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.