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, 20597-20599 [E6-5980]

Download as PDF Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Proposed Rules 20597 Actions Compliance Procedures (1) Modify the fuel system to improve the venting between the collector tank, the main wing tanks, and the engine. (i) For Group 1 Airplanes: Within the next 3 calendar months after July 13, 1998 (the effective date of AD 98–12–01), unless already done. (ii) For Group 2 Airplanes: Within the next 3 calendar months after the effective date of this AD, unless already done. For all airplanes: As of the effective date of this AD. Follow Pilatus PC–6 Service Bulletin No. PC– 6–SB–171, dated October 18, 1995. (2) Do not install any collector tank or fuel vent system unless the modification requirements of paragraph (e)(1) are done. 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 98–12–01 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. To get copies of the documents referenced 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, or on the Internet at https:// dms.dot.gov. The docket number is Docket No. FAA–2006–24091; Directorate Identifier 2006–CE–17–AD. Issued in Kansas City, Missouri, on April 17, 2006. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–5978 Filed 4–20–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24090; Directorate Identifier 2006–CE–16–AD] wwhite on PROD1PC61 with PROPOSALS 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: VerDate Aug<31>2005 16:10 Apr 20, 2006 Jkt 208001 Notice of proposed rulemaking (NPRM). ACTION: SUMMARY: We propose to supersede Airworthiness Directive (AD) 2002–21– 08, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC–6 airplanes. AD 2002–21–08 currently requires you to inspect the aileron assembly for correct configuration and modify as necessary. Since we issued AD 2002–21–08, the FAA determined the action should also apply to all the models of the PC–6 airplanes listed in the type certification data sheet of Type Certificate (TC) No. 7A15 that are produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In addition, the intent of the applicability of AD 2002–21–08 was to apply to all the affected serial numbers of the airplane models listed in TC No. 7A15. Consequently, this proposed AD would retain all the actions of AD 2002–21–08, would add those Fairchild Republic Company airplanes to the applicability of this proposed AD, and would list out the individual specific airplane models. We are proposing this AD to correct improper aileron assembly configuration, which could result in failure of the aileron mass balance weight. Such failure could lead to loss of control of the airplane. DATES: We must receive comments on this proposed AD by May 24, 2006. 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, PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 Follow Pilatus PC–6 Service Bulletin No. PC– 6–SB–171, dated October 18, 1995. Room PL–401, Washington, DC 20590– 0001. • 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 this proposed AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224. 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: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2006–24090; Directorate Identifier 2006–CE–16–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 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 report of an unapproved mass balance weight installation and an improper aileron configuration (a result of improper configuration control and tracking) on Pilatus Model PC–6 airplanes caused us to issue AD 2002– 21–08, Amendment 39–12914 (67 FR 64520, October 21, 2002). AD 2002–21– E:\FR\FM\21APP1.SGM 21APP1 20598 Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Proposed Rules 08 currently requires you to inspect the aileron assembly for correct configuration and modify as necessary (on certain Model PC–6 airplanes). The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, notified the FAA of the need to supersede AD 2002– 21–08 to address an unsafe condition that may exist or could develop on certain Model PC–6 airplanes. The FOCA reports that the AD action should also apply to all the models of the PC– 6 airplanes listed in the type certification data sheet of TC No. 7A15 produced in the United States through a licensing agreement between Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). This condition, if not corrected, could result in failure of the aileron mass balance weights. Such failure could lead to loss of control of the airplane. Foreign Airworthiness Authority Information The FOCA recently issued Swiss AD Number HB 2005–289, effective date August 23, 2005, to ensure the continued airworthiness of all models of the PC–6 airplanes listed in TC No. 7A15, including those produced in the United States under a licensing agreement with Pilatus and Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). The State of Design for the Pilatus PC–6 airplanes is Switzerland and the airplanes are 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 airworthiness agreement. Under this bilateral airworthiness agreement, the FOCA has kept us informed of the situation described above. FAA’s Determination and Requirements of the Proposed AD We are proposing this AD because we have examined the FOCA’s findings, evaluated all information and determined the unsafe condition described previously is likely to exist or develop on other products of the same Parts cost 1 work hour × $80 per hour = $80 ....................... Not Applicable ............... Parts cost wwhite on PROD1PC61 with PROPOSALS 16 work hours × $80 per hour = $1,280 ..................................... 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. VerDate Aug<31>2005 16:10 Apr 20, 2006 Jkt 208001 $80 be required based on the results of the proposed inspection. We have no way of Labor cost $419 Fmt 4702 Sfmt 4702 Total cost on U.S. operators 49 × $80 = $3,920. determining the number of airplanes that may need such modification: $1,280 + $419 = $1,699. 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. Frm 00025 We estimate that this proposed AD would affect 49 airplanes in the U.S. registry. We estimate the following costs to do the proposed inspection: Total cost per airplane Regulatory Findings PO 00000 Costs of Compliance Total cost per airplane Labor cost We estimate the following costs to do any necessary modifications that would type design that are certificated for operation in the United States. This proposed AD would supersede AD 2002–21–08 with a new AD that would retain all the actions of AD 2002– 21–08 and would: • Add manufacturer serial numbers (MSN) 2001 through 2092 for all the models of the PC–6 airplanes as listed in TC No. 7A15 and specified in the applicability section. These MSN are the airplanes produced in the United States through a licensing agreement with the Fairchild Republic Company; and • List all the models of the PC–6 airplanes as listed in TC No. 7A15. 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. E:\FR\FM\21APP1.SGM 21APP1 Federal Register / Vol. 71, No. 77 / Friday, April 21, 2006 / Proposed Rules 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2002–21–08, Amendment 39–12914, and adding the following new AD: Pilatus Aircraft Ltd.: Docket No. FAA–2006– 24090; Directorate Identifier 2006–CE– 16–AD. Comments Due Date (a) We must receive comments on this airworthiness directive (AD) action by May 24, 2006. Affected ADs (b) This AD supersedes AD 2002–21–08, Amendment 39–12914. Applicability (c) This AD affects the following 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 and serial numbers that are certificated in any category: (1) Group 1 (maintains the actions from AD 2002–21–08): All manufacturer serial numbers (MSN) up to and including 939. (2) Group 2: MSN 2001 through 2092. Note: These airplanes are also identified as Fairchild Republic Company PC–6 airplanes, 20599 Fairchild Heli Porter PC–6 airplanes, or Fairchild-Hiller Corporation PC–6 airplanes. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland that requires the actions of AD 2002–21–08 for the added MSN 2001 through 2092 for all the models of the PC–6 airplanes listed in the type certificate data sheet of Type Certificate (TC) No. 7A15. We are issuing this AD to correct improper aileron assembly configuration, which could result in failure of the aileron mass balance weight. Such failure could lead to loss of control of the airplane. Compliance (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect the aileron assembly for proper configuration. (i) For Group 1 Airplanes: Within the next 30 days after December 6, 2002 (the effective date of AD 2002–21–08), unless already done. (ii) For Group 2 Airplanes: Within the next 30 days after the effective date of this AD, unless already done. For All Airplanes: Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. Follow Pilatus Service Bulletin No. 62B, dated May 1967, as specified in Pilatus PC–6 Service Bulletin No. 57–001, dated December 20, 2001. For All Airplanes: Before further flight after the inspection required in paragraph (e)(1) of this AD, unless already done. Follow Pilatus PC–6 Service Bulletin No. 57– 001, dated December 20, 2001. (2) If the aileron assembly configuration incorporates aileron part number (P/N) 6106.10.xxx or P/N 6106.0010.xxx, modify the assembly following Pilatus Service Bulletin No. 62B, dated May 1967, and install a placard. (3) If the aileron assembly configuration differs from that specified in Pilatus Service Bulletin No. 62B, dated May 1967, or if the part numbers are missing and cannot be verified: (i) Obtain a repair scheme from the manufacturer through the FAA at the address specified in paragraph (f) of this AD; and (ii) Incorporate this repair scheme. (4) Do not install any aileron assembly unless the inspection, modification, placard, and repair requirements (as applicable) of paragraphs (e)(1), (e)(2), (e)(3), (e)(3)(i), and (e)(3)(ii) of this AD are done. Alternative Methods of Compliance (AMOCs) wwhite on PROD1PC61 with PROPOSALS (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 alternative methods of compliance (AMOCs) for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 2002–21–08 are approved for this AD. Related Information (h) Swiss Airworthiness Directive Number HB 2005–289, effective date August 23, 2005, also addresses the subject of this AD. To get copies of the documents referenced in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, VerDate Aug<31>2005 16:10 Apr 20, 2006 Jkt 208001 Follow Pilatus Service Bulletin No. 62B, dated May 1967, as specified in Pilatus PC–6 Service Bulletin No. 57–001, dated December 20, 2001. (i) For Group 1 Airplanes: As of December 6, Follow Pilatus PC–6 Service Bulletin No. 57– 2002 (the effective date of AD 2002–21–08). 001, dated December 20, 2001. (ii) For Group 2 Airplanes: As of the effective date of this AD. 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, or on the Internet at https://dms.dot.gov. The docket number is Docket No. FAA–2006–24090; Directorate Identifier 2006–CE–16–AD. Issued in Kansas City, Missouri, on April 17, 2006. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–5980 Filed 4–20–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24522; Directorate Identifier 2006–NM–002–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200 and –300, and A340–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: E:\FR\FM\21APP1.SGM 21APP1

Agencies

[Federal Register Volume 71, Number 77 (Friday, April 21, 2006)]
[Proposed Rules]
[Pages 20597-20599]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-5980]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24090; Directorate Identifier 2006-CE-16-AD]
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).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2002-21-
08, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-6
airplanes. AD 2002-21-08 currently requires you to inspect the aileron
assembly for correct configuration and modify as necessary. Since we
issued AD 2002-21-08, the FAA determined the action should also apply
to all the models of the PC-6 airplanes listed in the type
certification data sheet of Type Certificate (TC) No. 7A15 that are
produced in the United States through a licensing agreement between
Pilatus and Fairchild Republic Company (also identified as Fairchild
Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation). In
addition, the intent of the applicability of AD 2002-21-08 was to apply
to all the affected serial numbers of the airplane models listed in TC
No. 7A15. Consequently, this proposed AD would retain all the actions
of AD 2002-21-08, would add those Fairchild Republic Company airplanes
to the applicability of this proposed AD, and would list out the
individual specific airplane models. We are proposing this AD to
correct improper aileron assembly configuration, which could result in
failure of the aileron mass balance weight. Such failure could lead to
loss of control of the airplane.

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

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 20590-0001.
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 this proposed AD, contact
Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 63 19; facsimile: +41 41 619 6224.

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:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include the docket number, ``FAA-
2006-24090; Directorate Identifier 2006-CE-16-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 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 report of an unapproved mass balance weight installation and an
improper aileron configuration (a result of improper configuration
control and tracking) on Pilatus Model PC-6 airplanes caused us to
issue AD 2002-21-08, Amendment 39-12914 (67 FR 64520, October 21,
2002). AD 2002-21-

[[Page 20598]]

08 currently requires you to inspect the aileron assembly for correct
configuration and modify as necessary (on certain Model PC-6
airplanes).
The Federal Office for Civil Aviation (FOCA), which is the
airworthiness authority for Switzerland, notified the FAA of the need
to supersede AD 2002-21-08 to address an unsafe condition that may
exist or could develop on certain Model PC-6 airplanes. The FOCA
reports that the AD action should also apply to all the models of the
PC-6 airplanes listed in the type certification data sheet of TC No.
7A15 produced in the United States through a licensing agreement
between Pilatus and Fairchild Republic Company (also identified as
Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller
Corporation).
This condition, if not corrected, could result in failure of the
aileron mass balance weights. Such failure could lead to loss of
control of the airplane.

Foreign Airworthiness Authority Information

The FOCA recently issued Swiss AD Number HB 2005-289, effective
date August 23, 2005, to ensure the continued airworthiness of all
models of the PC-6 airplanes listed in TC No. 7A15, including those
produced in the United States under a licensing agreement with Pilatus
and Fairchild Republic Company (also identified as Fairchild
Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation).
The State of Design for the Pilatus PC-6 airplanes is Switzerland
and the airplanes are 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 airworthiness
agreement.
Under this bilateral airworthiness agreement, the FOCA has kept us
informed of the situation described above.

FAA's Determination and Requirements of the Proposed AD

We are proposing this AD because we have examined the FOCA's
findings, evaluated all information and determined the unsafe condition
described previously is likely to exist or develop on other products of
the same type design that are certificated for operation in the United
States.
This proposed AD would supersede AD 2002-21-08 with a new AD that
would retain all the actions of AD 2002-21-08 and would:
Add manufacturer serial numbers (MSN) 2001 through 2092
for all the models of the PC-6 airplanes as listed in TC No. 7A15 and
specified in the applicability section. These MSN are the airplanes
produced in the United States through a licensing agreement with the
Fairchild Republic Company; and
List all the models of the PC-6 airplanes as listed in TC
No. 7A15.

Costs of Compliance

We estimate that this proposed AD would affect 49 airplanes in the
U.S. registry.
We estimate the following costs to do the proposed inspection:

----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $80 per hour = $80...... Not Applicable........... $80 49 x $80 = $3,920.
----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary modifications
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that may need
such modification:

------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
------------------------------------------------------------------------
16 work hours x $80 per hour = $419 $1,280 + $419 = $1,699.
$1,280.
------------------------------------------------------------------------

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 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.

[[Page 20599]]

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 removing Airworthiness Directive
(AD) 2002-21-08, Amendment 39-12914, and adding the following new AD:

Pilatus Aircraft Ltd.: Docket No. FAA-2006-24090; Directorate
Identifier 2006-CE-16-AD.

Comments Due Date

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

Affected ADs

(b) This AD supersedes AD 2002-21-08, Amendment 39-12914.

Applicability

(c) This AD affects the following 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 and serial numbers that are certificated in any
category:
(1) Group 1 (maintains the actions from AD 2002-21-08): All
manufacturer serial numbers (MSN) up to and including 939.
(2) Group 2: MSN 2001 through 2092.

Note: These airplanes are also identified as Fairchild Republic
Company PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or
Fairchild-Hiller Corporation PC-6 airplanes.

Unsafe Condition

(d) This AD results from mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland that requires the actions of AD 2002-21-08 for the added
MSN 2001 through 2092 for all the models of the PC-6 airplanes
listed in the type certificate data sheet of Type Certificate (TC)
No. 7A15. We are issuing this AD to correct improper aileron
assembly configuration, which could result in failure of the aileron
mass balance weight. Such failure could lead to loss of control of
the airplane.

Compliance

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

------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the aileron (i) For Group 1 Follow Pilatus
assembly for proper Airplanes: Within Service Bulletin
configuration. the next 30 days No. 62B, dated May
after December 6, 1967, as specified
2002 (the effective in Pilatus PC-6
date of AD 2002-21- Service Bulletin
08), unless already No. 57-001, dated
done. December 20, 2001.
(ii) For Group 2
Airplanes: Within
the next 30 days
after the effective
date of this AD,
unless already done.
(2) If the aileron assembly For All Airplanes: Follow Pilatus
configuration incorporates Before further Service Bulletin
aileron part number (P/N) flight after the No. 62B, dated May
6106.10.xxx or P/N inspection required 1967, as specified
6106.0010.xxx, modify the in paragraph (e)(1) in Pilatus PC-6
assembly following Pilatus of this AD, unless Service Bulletin
Service Bulletin No. 62B, already done. No. 57-001, dated
dated May 1967, and install December 20, 2001.
a placard.
(3) If the aileron assembly For All Airplanes: Follow Pilatus PC-6
configuration differs from Before further Service Bulletin
that specified in Pilatus flight after the No. 57-001, dated
Service Bulletin No. 62B, inspection required December 20, 2001.
dated May 1967, or if the in paragraph (e)(1)
part numbers are missing of this AD, unless
and cannot be verified: already done.
(i) Obtain a repair scheme
from the manufacturer
through the FAA at the
address specified in
paragraph (f) of this AD;
and
(ii) Incorporate this repair
scheme.
(4) Do not install any (i) For Group 1 Follow Pilatus PC-6
aileron assembly unless the Airplanes: As of Service Bulletin
inspection, modification, December 6, 2002 No. 57-001, dated
placard, and repair (the effective date December 20, 2001.
requirements (as of AD 2002-21-08).
applicable) of paragraphs (ii) For Group 2
(e)(1), (e)(2), (e)(3), Airplanes: As of
(e)(3)(i), and (e)(3)(ii) the effective date
of this AD are done. 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 alternative methods of
compliance (AMOCs) for this AD, if requested using the procedures
found in 14 CFR 39.19.
(g) AMOCs approved for AD 2002-21-08 are approved for this AD.

Related Information

(h) Swiss Airworthiness Directive Number HB 2005-289, effective
date August 23, 2005, also addresses the subject of this AD. To get
copies of the documents referenced 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, or on the Internet at https://dms.dot.gov. The
docket number is Docket No. FAA-2006-24090; Directorate Identifier
2006-CE-16-AD.

Issued in Kansas City, Missouri, on April 17, 2006.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-5980 Filed 4-20-06; 8:45 am]
BILLING CODE 4910-13-P

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