### 43807 Federal Register / Vol. 75, No. 143 / Tuesday, July 27, 2010 / Rules and Regulations

reference of Boeing Alert Service Bulletin 737–57A1277, Revision 1, dated November 25, 2003, on December 4, 2003 (68 FR 67027, December 1, 2003).

(3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com.

(4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call
425–227–1221.

(5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go
to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Renton, Washington, on July 14,
2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–18009 Filed 7–26–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0729; Directorate Identifier 2010–CE–032–AD; Amendment**  **39–16373; AD 2010–15–07]**

**RIN 2120–AA64**

**Airworthiness Directives; Zaklad Szybowcowy**  ‘‘ **Jez  ̇**  **o**

** ́ w**  ’’ **Henryk Mynarski Model PW–6U Sailplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Cracks on the lug of the rear attachment fitting of the horizontal stabilizer have been detected during the inspection of two PW–6U gliders operated by the same user.

This condition, if not corrected, could result in no longer retaining the horizontal stabilizer in place and consequent loss of control of the aeroplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.

**DATES :**  This AD becomes effective August 16, 2010.

On August 16, 2010, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD.

We must receive comments on this AD by September 10, 2010.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: (202) 493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816)
329–4090.

**SUPPLEMENTARY INFORMATION :** 

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2010– 0108–E, dated June 8, 2010 (referred to after this as ‘‘ the MCAI ’’ ), to correct an unsafe condition for the specified products. The MCAI states:

Cracks on the lug of the rear attachment fitting of the horizontal stabilizer have been detected during the inspection of two PW–6U gliders operated by the same user.

This condition, if not corrected, could result in no longer retaining the horizontal stabilizer in place and consequent loss of control of the aeroplane.

For the reasons described above, this AD requires immediate and periodic inspections of the horizontal stabilizer rear attachment fitting and the accomplishment of the relevant corrective actions as necessary. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Zak5 ad Szybowcowy ‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski has issued Mandatory Bulletin BO–78–10–10, dated June 7, 2010. 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 AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might have also required 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 AD. These requirements take precedence over those copied from the MCAI.

FAA’s Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because cracks on the lug of the rear attachment fitting of the horizontal stabilizer have been found. This condition, if not detected and corrected,


### 43808 Federal Register / Vol. 75, No. 143 / Tuesday, July 27, 2010 / Rules and Regulations

could cause the horizontal stabilizer to fail, which could result in loss of control. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘ Docket No. FAA–2010–0729; Directorate Identifier 2010–CE–032–AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘ Subtitle VII: Aviation Programs, ’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘ Subtitle VII, Part A, Subpart III, Section 44701: General requirements. ’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD:

(1) Is not a ‘‘ significant regulatory action ’’ under Executive Order 12866;

(2) Is not a ‘‘ significant rule ’’ under 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 AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment

■ Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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:

2010–15–07 Zak 5 ad Szybowcowy ‘‘ Jez  ̇ o

 ́ w ’’ Henryk Mynarski: Amendment 39– 16373; Docket No. FAA–2010–0729; Directorate Identifier 2010–CE–032–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective August 16, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to the following Zak 5 ad Szybowcowy ‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski Model PW–6U sailplanes, certificated in any category:

(i) Serial numbers (S/Ns) 78.00.00 through 78.03.07 equipped with an automatic elevator control connection installed in accordance with Zak 5 ad Szybowcowy

‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski Bulletin BS–78– 02–04;

(ii) S/Ns 78.03.08 through 78.03.10; and (iii) S/Ns 78.04.01 and subsequent S/Ns.
Subject

(d) Air Transport Association of America (ATA) Code 27: Flight Controls.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states: Cracks on the lug of the rear attachment fitting of the horizontal stabilizer have been detected during the inspection of two PW–6U gliders operated by the same user.

This condition, if not corrected, could result in no longer retaining the horizontal stabilizer in place and consequent loss of control of the aeroplane.

For the reasons described above, this AD requires immediate and periodic inspections of the horizontal stabilizer rear attachment fitting and the accomplishment of the relevant corrective actions as necessary.
Actions and Compliance

(f) Unless already done, do the following actions.

(1) Before further flight after the effective date of this AD, repetitively thereafter atintervals not to exceed 50 hours time-inservice, and, in addition, before further flight anytime the sailplane experiences a ‘‘ hard landing, ’’ visually inspect the rear attachment fitting of the horizontal stabilizer for cracks and damage. Do the inspections following Zak 5 ad Szybowcowy ‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski Mandatory Bulletin BO–78–10–10, dated June 7, 2010, except use a 10X magnifier.

(2) If any crack or damage is found during any inspection required in paragraph (f)(1) of this AD, before further flight after the inspection in which a crack or damage is found, contact Zak 5 ad Szybowcowy ‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski, ul. D 5 uga 93, 58–521 Jez  ̇ o

 ́ w Sudecki, Poland, telephone/fax: +48 75 713 21 59 or +48 33 829 33 72; e-mail: szdjezow.com.pl, to obtain an FAA-approved repair scheme and incorporate the repair scheme.

FAA AD Differences

Note: This AD differs from the MCAI and/ or service information as follows. The service information requires a visual inspection with a 5X magnifier. For the inspection, we are requiring a 10X magnifier to detect cracks and damage that may go undetected using only a 5X magnifier.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329– 4090. Before using any approved AMOC on any sailplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.


### 43809 Federal Register / Vol. 75, No. 143 / Tuesday, July 27, 2010 / Rules and Regulations

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(h) Refer to MCAI EASA AD No. 2010– 0108–E, dated June 8, 2010, and Zak 5 ad Szybowcowy ‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski Mandatory Bulletin BO–78–10–10, dated June 7, 2010, for related information.
Material Incorporated by Reference

(i) You must use Zak 5 ad Szybowcowy

‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski Mandatory Bulletin BO–78–10–10, dated June 7, 2010, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Zak 5 ad Szybowcowy ‘‘Jez  ̇ o

 ́ w ’’ Henryk Mynarski, ul. D 5 uga 93, 58–521 Jez  ̇ o

 ́ w Sudecki, Poland, telephone/fax: +48 75 713 21 59 or +48 33 829 33 72; e-mail: szdjezow.com.pl; Internet: http:// www.szdjezow.com.pl/.

(3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768.

(4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go
to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ ibr

_locations.html. Issued in Kansas City, Missouri on July 15,
2010. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–17924 Filed 7–26–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–1015; Directorate Identifier 2009–CE–039–AD; Amendment**  **39–16376; AD 2010–15–10]**

**RIN 2120–AA64**

**Airworthiness Directives; Piper Aircraft, Inc. PA–28, PA–32, PA–34,**  **and PA–44 Series Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), DOT. **ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) PA–28, PA– 32, PA–34, and PA–44 series airplanes. This AD requires you to inspect the control wheel shaft on both the pilot and copilot sides and, if necessary, replace the control wheel shaft. This AD results from two field reports of incorrectly assembled control wheel shafts. We are issuing this AD to detect and correct any incorrectly assembled control wheel shafts. This condition, if left uncorrected, could lead to separation of the control wheel shaft, resulting in loss of pitch and roll control.

**DATES :**  This AD becomes effective on August 31, 2010.

On August 31, 2010, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD.

**ADDRESSES :**  To get the service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978–6573; Internet: http:// www.newpiper.com/company/ publications.asp.

To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at http:// www.regulations.gov. The docket number is FAA–2009–1015; Directorate Identifier 2009–CE–039–AD.

**FOR FURTHER INFORMATION CONTACT :**  Hector Hernandez, Aerospace Engineer, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; telephone: (404) 474–5587; fax: (404) 474–5606.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On October 23, 2009, 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 certain Piper Aircraft, Inc. (Piper) PA– 28, PA–32, PA–34, and PA–44 series airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on October 30, 2009 (74 FR 56138). The NPRM proposed to detect and correct any incorrectly assembled control wheel shafts.

Comments

We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA’s response to each comment: Comment Issue No. 1: Difficulty in Disassembling Components

Fifteen commenters, including the Aircraft Owners and Pilots Association (AOPA), Barry Rogers, Bruce Chien, and Harry Cook commented that some Piper airplanes do not have inspection holes and may require disassembly of the control wheel shaft. Disassembly can take several hours due to the difficulty in removing (or separating) the parts, which could be very costly and possibly damage a perfectly good component.

We infer from these comments that the commenters want us to rescind the NPRM due to difficulty in disassembling the parts and cost of labor for disassembly.

The FAA partially agrees with the above comment. We disagree that we should rescind the NPRM due to difficulty in disassembling the parts. According to Piper, the universal joint has rotating parts that wear, and replacement of those parts, which requires disassembly, is a routine procedure done with little difficulty. Piper sales history records show, that on average, they sell over 400 of these as service spare replacements each year, and the Piper technical support department is not aware of anyone reporting difficulty in replacing them. Piper has revised their service bulletin, to provide more information about the different control wheel shaft configurations. We agree that disassembly of the control shaft wheel may take more time than an inspection with witness holes. However, the FAA has determined that there is an unsafe condition and has identified actions to correct that unsafe condition. It is every owner’s and operator’s responsibility to maintain the airplane to the type design and address any airworthiness concerns. This includes all maintenance requirements and ADs that correct an unsafe condition.

We will change the final rule AD action to include Piper Aircraft, Inc. Mandatory Service Bulletin No. 1197B, dated May 3, 2010, to use for the procedures to comply with the actions required by this AD. We will allow

‘‘ unless already done ’’ credit to anyone who already accomplished the actions following the previous service bulletin included as part of the NPRM. Comment Issue No. 2: Cost Absorbed by Piper

John Witosky, Thomas McIntosh, Claude Dalrymple, Jr., M. Hefter, and George Haffey commented that the cost