Airworthiness Directives; Pilatus Aircraft Limited Models B4-PC11, B4-PC11A, and B4-PC11AF Sailplanes, 20708-20710 [05-7563]

Download as PDF 20708 Federal Register / Vol. 70, No. 76 / Thursday, April 21, 2005 / Rules and Regulations perform critical functions. The term ‘‘critical’’ means those functions whose failure would contribute to, or cause, a failure condition that would prevent the continued safe flight and landing of the airplane. The systems identified by the hazard analysis that perform critical functions are candidates for the application of HIRF requirements. A system may perform both critical and non-critical functions. Primary electronic flight display systems, and their associated components, perform critical functions such as attitude, altitude, and airspeed indication. The HIRF requirements apply only to critical functions. Compliance with HIRF requirements may be demonstrated by tests, analysis, models, similarity with existing systems, or any combination of these. Service experience alone is not acceptable since normal flight operations may not include an exposure to the HIRF environment. Reliance on a system with similar design features for redundancy as a means of protection against the effects of external HIRF is generally insufficient since all elements of a redundant system are likely to be exposed to the fields concurrently. Applicability As discussed above, these special conditions are applicable to the Cessna 182T and T182T airplanes with the Garmin GFC–700 digital autopilot. Should Garmin International Inc. apply later for a Supplemental Type Certificate on another model on the same type certification data sheet to incorporate the same novel or unusual design feature, the special conditions would apply to that model as well under the provisions of § 21.101. Conclusion This action affects only certain novel or unusual design features on the Cessna 182T and T182T airplanes. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on the airplane. The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. For this reason, and because a delay would significantly affect the certification of the airplane, which is imminent, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for VerDate jul<14>2003 16:25 Apr 20, 2005 Jkt 205001 adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 23 Aircraft, Aviation safety, Signs and symbols. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–20006; Directorate Identifier 2004–CE–49–AD; Amendment 39– 14059; AD 2005–08–07] RIN 2120–AA64 Citation Airworthiness Directives; Pilatus Aircraft Limited Models B4–PC11, B4– PC11A, and B4–PC11AF Sailplanes The authority citation for these special conditions is as follows: AGENCY: I Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.101; and 14 CFR 11.38 and 11.19. PART 23—AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the Cessna 182T and T182T airplanes to include a Garmin GFC–700 Autopilot system. 1. Protection of Electrical and Electronic Systems from High Intensity Radiated Fields (HIRF). Each system that performs critical functions must be designed and installed to ensure that the operations, and operational capabilities of these systems to perform critical functions are not adversely affected when the airplane is exposed to high intensity radiated electromagnetic fields external to the airplane. 2. For the purpose of these special conditions, the following definition applies: Critical Functions: Functions whose failure would contribute to, or cause, a failure condition that would prevent the continued safe flight and landing of the airplane. I Issued in Kansas City, Missouri on April 8, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7977 Filed 4–20–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA adopts a new airworthiness directive (AD) for all Pilatus Aircraft Limited (Pilatus) Models B4–PC11, B4–PC11A, and B4–PC11AF sailplanes. This AD requires you to repetitively inspect the control-column support for cracks and, if any cracks are found, replace the control-column support with a new support. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct cracks in the controlcolumn support, which could result in failure of the support. This failure could lead to loss of the primary flight control system. DATES: This AD becomes effective on June 2, 2005. As of June 2, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH–6371 Stans, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; email: fodermatt@pilatus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465–9099; facsimile: (303) 465–6040. 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 https:// dms.dot.gov. The docket number is FAA–2004–20006; Directorate Identifier 2004–CE–49–AD. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, E:\FR\FM\21APR1.SGM 21APR1 Federal Register / Vol. 70, No. 76 / Thursday, April 21, 2005 / Rules and Regulations Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion What events have caused this AD? The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, recently notified FAA that an unsafe condition may exist on all Pilatus Aircraft Limited (Pilatus) Models B4–PC11, B4–PC11A, and B4–PC11AF sailplanes. The FOCA reports nine occurrences of cracks in the support of the control-column (part number (P/N) 112.35.11.072). What is the potential impact if FAA took no action? Cracks in the controlcolumn support could result in failure and lead to loss of the primary flight control system. Has FAA taken any action to this point? We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Pilatus Aircraft Limited (Pilatus) Models B4– PC11, B4–PC11A, and B4–PC11AF sailplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on February 11, 2005 (70 FR 7217). The NPRM proposed to require you to repetitively inspect the control-column support for cracks and, if any cracks are found, replace the control-column support with a new support. Comments Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion What is FAA’s final determination on this issue? We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for 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. Changes to 14 CFR Part 39—Effect on the AD How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA’s AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Costs of Compliance How many sailplanes does this AD impact? We estimate that this AD affects 32 sailplanes in the U.S. registry. What is the cost impact of this AD on owners/operators of the affected sailplanes? We estimate the following costs to do the inspection of the controlcolumn support: Total cost per sailplane Labor cost Parts cost 1 work hour × $65 per hour = $65 ................................................... Not applicable ............................. We estimate the following costs to do any necessary replacements that would be required based on the results of this inspection. We have no way of determining the number of sailplanes VerDate jul<14>2003 16:25 Apr 20, 2005 Jkt 205001 Parts cost that is likely to exist or develop on products identified in this AD. Regulatory Findings Will this AD impact various entities? We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Will this AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and PO 00000 Frm 00017 32 × $65 = $2,080 that may need this replacement of the control-column support: 5 work hours × $65 per hour = $325 .................................................................................................................... What authority does FAA have for issuing this rulemaking action? Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition Total cost on U.S. operators $65 Labor cost Authority for This Rulemaking Fmt 4700 Sfmt 4700 20709 Total cost per sailplane $250 $575 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–2004–20006; Directorate Identifier 2004–CE–49–AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. E:\FR\FM\21APR1.SGM 21APR1 20710 Federal Register / Vol. 70, No. 76 / Thursday, April 21, 2005 / Rules and Regulations Adoption of the Amendment 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 When Does This AD Become Effective? (a) This AD becomes effective on June 2, 2005. What Other ADs Are Affected by This Action? 1. The authority citation for part 39 continues to read as follows: I (b) None. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to detect and correct cracks in the control-column support, which could result in failure of the support. This failure could lead to loss of the primary flight control system. [Amended] 2. FAA amends § 39.13 by adding a new AD to read as follows: I What Sailplanes Are Affected by This AD? What Must I Do To Address This Problem? (c) This AD affects Models B4–PC11, B4– PC11A, and B4–PC11AF sailplanes, all serial numbers, that are certificated in any category. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 2005–08–07 Pilatus Aircraft Limited: Amendment 39–14059; Docket No. FAA–2004–20006; Directorate Identifier 2004–CE–49–AD. (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect the control-column support (part number (P/N) 112.35.11.072) for cracks. Initially inspect within 12 calendar months after the last inspection under Pilatus Aircraft Ltd. Service Bulletin No. 1005, Revision No. 1, dated April 9, 2003, or Pilatus Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004, where no cracks were found or within the next 30 days after June 2, 2005 (the effective date of this AD), whichever occurs later, unless already done. Repetitively inspect 2004. thereafter at intervals not to exceed every 12 calendar months regardless of whether the control-column support was replaced. Before further flight after the inspection required by paragraph (e)(1) of this AD where you found the crack. Continue the repetitive inspections required by paragraph (e)(1) of this AD. Follow Pilatus B4–PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004. PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004. 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 6208; facsimile: +41 41 619 7311; email: fodermatt@pilatus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465–9099; facsimile: (303) 465–6040. 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at https:// dms.dot.gov. The docket number is FAA– 2004–20006; Directorate Identifier 2004–CE– 49–AD. Issued in Kansas City, Missouri, on April 11, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7563 Filed 4–20–05; 8:45 am] (2) If any cracks are found after the inspection required by paragraph (e)(1) of this AD, replace the control-column support (P/N 112.35.11.072) with a new control-column support (P/N 112.35.11.072). May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; facsimile: (816) 329–4090. May I Obtain a Special Flight Permit for the Initial Inspection Requirement of This AD? (g) No. Special flight permits are not allowed for this AD. Is There Other Information That Relates to This Subject? (h) Swiss AD Number HB 2004–491, dated December 23, 2004, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (i) You must do the actions required by this AD following the instructions in Pilatus B4– VerDate jul<14>2003 16:25 Apr 20, 2005 Jkt 205001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Follow Pilatus B4–PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2003–CE–65–AD; Amendment 39–14065; AD 2005–08–13] RIN 2120–AA64 Airworthiness Directives; Glaser-Dirks Flugzeugbau GmbH Model DG–800B Sailplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for all Glaser-Dirks Flugzeugbau GmbH (DG Flugzeugbau) Model DG–800B E:\FR\FM\21APR1.SGM 21APR1

Agencies

[Federal Register Volume 70, Number 76 (Thursday, April 21, 2005)]
[Rules and Regulations]
[Pages 20708-20710]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-7563]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-20006; Directorate Identifier 2004-CE-49-AD; 
Amendment 39-14059; AD 2005-08-07]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Limited Models B4-
PC11, B4-PC11A, and B4-PC11AF Sailplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA adopts a new airworthiness directive (AD) for all 
Pilatus Aircraft Limited (Pilatus) Models B4-PC11, B4-PC11A, and B4-
PC11AF sailplanes. This AD requires you to repetitively inspect the 
control-column support for cracks and, if any cracks are found, replace 
the control-column support with a new support. This AD results from 
mandatory continuing airworthiness information (MCAI) issued by the 
airworthiness authority for Switzerland. We are issuing this AD to 
detect and correct cracks in the control-column support, which could 
result in failure of the support. This failure could lead to loss of 
the primary flight control system.

DATES: This AD becomes effective on June 2, 2005.
    As of June 2, 2005, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in the 
regulation.

ADDRESSES: To get the service information identified in this AD, 
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, 
Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; 
email: fodermatt@pilatus-aircraft.com or from Pilatus Business Aircraft 
Ltd., Product Support Department, 11755 Airport Way, Broomfield, 
Colorado 80021; telephone: (303) 465-9099; facsimile: (303) 465-6040.
    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 https://
dms.dot.gov. The docket number is FAA-2004-20006; Directorate 
Identifier 2004-CE-49-AD.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,

[[Page 20709]]

Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Discussion

    What events have caused this AD? The Federal Office for Civil 
Aviation (FOCA), which is the airworthiness authority for Switzerland, 
recently notified FAA that an unsafe condition may exist on all Pilatus 
Aircraft Limited (Pilatus) Models B4-PC11, B4-PC11A, and B4-PC11AF 
sailplanes. The FOCA reports nine occurrences of cracks in the support 
of the control-column (part number (P/N) 112.35.11.072).
    What is the potential impact if FAA took no action? Cracks in the 
control-column support could result in failure and lead to loss of the 
primary flight control system.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to all Pilatus Aircraft Limited 
(Pilatus) Models B4-PC11, B4-PC11A, and B4-PC11AF sailplanes. This 
proposal was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on February 11, 2005 (70 FR 7217). The NPRM proposed 
to require you to repetitively inspect the control-column support for 
cracks and, if any cracks are found, replace the control-column support 
with a new support.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. We received no 
comments on the proposal or on the determination of the cost to the 
public.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for 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.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many sailplanes does this AD impact? We estimate that this AD 
affects 32 sailplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected sailplanes? We estimate the following costs to do the 
inspection of the control-column support:

----------------------------------------------------------------------------------------------------------------
                                                             Total cost per
             Labor cost                    Parts cost           sailplane       Total cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
1 work hour x $65 per hour = $65...  Not applicable........             $65  32 x $65 = $2,080
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of this inspection. We have 
no way of determining the number of sailplanes that may need this 
replacement of the control-column support:

------------------------------------------------------------------------
                                                        Total cost  per
               Labor cost                  Parts cost      sailplane
------------------------------------------------------------------------
5 work hours x $65 per hour = $325......         $250               $575
------------------------------------------------------------------------

Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106 describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this AD.

Regulatory Findings

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD will not have a substantial direct effect on the States, on the 
relationship between the national government and the States, or on the 
distribution of power and responsibilities among the various levels of 
government.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2004-20006; Directorate Identifier 2004-CE-49-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 20710]]

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2005-08-07 Pilatus Aircraft Limited: Amendment 39-14059; Docket No. 
FAA-2004-20006; Directorate Identifier 2004-CE-49-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on June 2, 2005.

What Other ADs Are Affected by This Action?

    (b) None.

What Sailplanes Are Affected by This AD?

    (c) This AD affects Models B4-PC11, B4-PC11A, and B4-PC11AF 
sailplanes, all serial numbers, that are certificated in any 
category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for 
Switzerland. The actions specified in this AD are intended to detect 
and correct cracks in the control-column support, which could result 
in failure of the support. This failure could lead to loss of the 
primary flight control system.

What Must I Do To Address This Problem?

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

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) Inspect the control-column    Initially inspect   Follow Pilatus B4-
 support (part number (P/N)        within 12           PC 11 Aircraft
 112.35.11.072) for cracks.        calendar months     Ltd. Service
                                   after the last      Bulletin No.
                                   inspection under    1005, Revision
                                   Pilatus Aircraft    No. 2, dated
                                   Ltd. Service        April 22, 2004.
                                   Bulletin No.
                                   1005, Revision
                                   No. 1, dated
                                   April 9, 2003, or
                                   Pilatus Aircraft
                                   Ltd. Service
                                   Bulletin No.
                                   1005, Revision
                                   No. 2, dated
                                   April 22, 2004,
                                   where no cracks
                                   were found or
                                   within the next
                                   30 days after
                                   June 2, 2005 (the
                                   effective date of
                                   this AD),
                                   whichever occurs
                                   later, unless
                                   already done.
                                   Repetitively
                                   inspect 2004.
                                   thereafter at
                                   intervals not to
                                   exceed every 12
                                   calendar months
                                   regardless of
                                   whether the
                                   control-column
                                   support was
                                   replaced.
(2) If any cracks are found       Before further      Follow Pilatus B4-
 after the inspection required     flight after the    PC 11 Aircraft
 by paragraph (e)(1) of this AD,   inspection          Ltd. Service
 replace the control-column        required by         Bulletin No.
 support (P/N 112.35.11.072)       paragraph (e)(1)    1005, Revision
 with a new control-column         of this AD where    No. 2, dated
 support (P/N 112.35.11.072).      you found the       April 22, 2004.
                                   crack. Continue
                                   the repetitive
                                   inspections
                                   required by
                                   paragraph (e)(1)
                                   of this AD.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Standards Office, Small 
Airplane Directorate, FAA. For information on any already approved 
alternative methods of compliance, contact Doug Rudolph, Aerospace 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, 
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: 
(816) 329-4090.

May I Obtain a Special Flight Permit for the Initial Inspection 
Requirement of This AD?

    (g) No. Special flight permits are not allowed for this AD.

Is There Other Information That Relates to This Subject?

    (h) Swiss AD Number HB 2004-491, dated December 23, 2004, also 
addresses the subject of this AD.

Does This AD Incorporate Any Material by Reference?

    (i) You must do the actions required by this AD following the 
instructions in Pilatus B4-PC 11 Aircraft Ltd. Service Bulletin No. 
1005, Revision No. 2, dated April 22, 2004. 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 6208; facsimile: +41 41 619 7311; email: 
fodermatt@pilatus-aircraft.com or from Pilatus Business Aircraft 
Ltd., Product Support Department, 11755 Airport Way, Broomfield, 
Colorado 80021; telephone: (303) 465-9099; facsimile: (303) 465-
6040. 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: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html or call (202) 741-6030. To view the AD docket, 
go to the Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-
401, Washington, DC 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2004-20006; Directorate 
Identifier 2004-CE-49-AD.

    Issued in Kansas City, Missouri, on April 11, 2005.
Nancy C. Lane,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7563 Filed 4-20-05; 8:45 am]
BILLING CODE 4910-13-P
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