## 35619 Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations

lower spar caps following paragraph (j)(2) of this AD to terminate the repetitive eddy current inspections required in paragraph (j)(4)(i) of this AD.

(5) If you have modified your airplane following paragraph (j)(1) of this AD prior to 3,200 hours TIS, you must do the following to reach the extended 8,000-hour TIS safe life:

(i) If you did not cold work the outboard two fastener holes in both the left and right hand lower spar caps following paragraph (j)(2) of this AD, you must do the repetitive eddy current inspections following paragraph (j)(4)(i) of this AD until you accumulate 4,800 hours TIS after the modification on the wing spar lower cap. Upon accumulation of 4,800 hours TIS after the modification on the wing spar lower cap, do the repetitive eddy current inspections at intervals not to exceed every 600 hours TIS until you reach the extended safe life of 8,000-hour TIS.

(ii) If you did cold work the outboard two fastener holes in both the left and right hand lower spar caps following paragraph (j)(2) of this AD, upon accumulation of 4,800 hours TIS after the modification on the wing spar lower cap do the repetitive eddy current inspections at intervals not to exceed every 600 hours TIS until you reach the 8,000-hour TIS safe life.

(6) For the initial and repetitive eddy current inspections required in paragraphs (j)(3), (j)(4)(i), (j)(5)(i) and (j)(5)(ii) of this AD, follow the instructions as specified in Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002. For any cracks found, follow the instructions for repair or replacement as specified in paragraph (g) of this AD.

(k) If any cracks are found as a result of any inspection required in paragraphs (e)(2), (j)(3), (j)4)(i), (j)(5)(i), and (j)(5)(ii) of this AD, report any cracks you find within 10 days after the cracks are found or within 10 days after April 21, 2006 (the effective date of AD 2006–08–09), whichever occurs later.

(1) Include in your report the aircraft SN, aircraft hours TIS, wing spar cap hours TIS, crack location and size, corrective action taken, and a point of contact name and phone number. Send your report to Andy McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO– 43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308– 3365; facsimile: (210) 308–3370.

(2) The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act and assigned OMB Control Number 2120–0056.
Special Permit Flight

(l) Under 14 CFR part 39.23, we are allowing special flight permits for the purpose of compliance with this AD under the following conditions:

(1) Only operate in day visual flight rules (VFR).

(2) Ensure that the hopper is empty. (3) Limit airspeed to 135 miles per hour (mph) indicated airspeed (IAS).

(4) Avoid any unnecessary g-forces. (5) Avoid areas of turbulence. (6) Plan the flight to follow the most direct
route. Alternative Methods of Compliance (AMOCs)

(m) The Manager, Fort Worth Airplane Certification Office, ASW–150, 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: Andy McAnaul, Aerospace Engineer, ASW–150, FAA San Antonio MIDO–43, 10100 Reunion Pl., Ste. 650, San Antonio, Texas 78216; telephone: (210) 308–3365; fax: (210) 308– 3370. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(n) AMOCs approved for AD 2006–08–09 are not approved for this AD.

Related Information

(o) To get copies of the service information referenced in this AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; fax: (940) 564– 5612; E-mail: airmail@airtractor.com; Internet: http://www.airtractor.com. 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.
Material Incorporated by Reference

(p) You must use Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Process Specification #204, Rev. C, dated November 16, 2004; Snow Engineering Co. Service Letter #215, page 5, titled ‘‘ 802 Spar Inspection Holes and Vent Tube Mod, ’’ dated November 19, 2003; Snow Engineering Co. Service Letter #240, dated September 30, 2004; Snow Engineering Co. Drawing Number 20975, Sheet 2, Rev. A, dated September 1, 2004; Snow Engineering Co. Drawing Number 20975, Sheet 3, dated January 6, 2005; and Snow Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28, 2004, to do the actions required by this AD, unless the AD specifies otherwise.

(1) On April 21, 2006 (71 FR 19994, April 19, 2006), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Process Specification #197, page 1, revised June 4, 2002; pages 2 through 4, dated February 23, 2001; and page 5, dated May 3, 2002; Snow Engineering Co. Process Specification #204, Rev. C, dated November 16, 2004; Snow Engineering Co. Service Letter #215, page 5, titled ‘‘ 802 Spar Inspection Holes and Vent Tube Mod, ’’ dated November 19, 2003; Snow Engineering Co. Service Letter #240, dated September 30, 2004; Snow Engineering Co. Drawing Number 20975, Sheet 2, Rev. A, dated September 1, 2004; Snow Engineering Co. Drawing Number 20975, Sheet 3, dated January 6, 2005; and Snow Engineering Co. Drawing 20995, Sheet 2, Rev. C, dated September 28, 2004, under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; fax: (940) 564–5612; E-mail: airmail@airtractor.com; Internet: http:// www.airtractor.com.

(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 June 15,
2010. Sandra J. Campbell, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2010–14990 Filed 6–22–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0122; Directorate Identifier 2009–CE–067–AD; Amendment**  **39–16338; AD 2010–13–07]**

**RIN 2120–AA64**



### Airworthiness Directives; Piper **Aircraft, Inc. Models PA–32R–301T and PA–46–350P Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA–32R– 301T and PA–46–350P airplanes. ThisAD requires you to replace any spotwelded, V-band exhaust coupling with a riveted, V-band exhaust coupling. ThisAD results from reports that spotwelded, V-band exhaust couplings are failing. We are issuing this AD to prevent failure of the V-band exhaust coupling, which could cause the exhaust pipe to detach from the turbocharger. This failure could result in release of high-temperature gases inside the engine compartment andpossibly cause an in-flight fire. An inflight fire could lead to loss of control.

**DATES** 

### : This AD becomes effective on July 28, 2010.


## 35620 Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations

On July 28, 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 Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone: (570) 323–6181; fax: (570) 327–7101; Internet: http://www.lycoming.com.

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–2010–0122; Directorate Identifier; 2009–CE–067–AD.

**FOR FURTHER INFORMATION CONTACT** 

### : Darby Mirocha, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, Georgia 30337; telephone:(404) 474–5573; fax: (404) 474–5606; email: darby.mirocha@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

On February 9, 2010, 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 Piper Aircraft, Inc. Models PA–32R– 301T and PA–46–350P airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on February 19, 2010 (75 FR 7407). The NPRM proposedto require replacing any spot-welded, Vband exhaust coupling with a riveted, V-band exhaust coupling.

Comments

We provided the public the opportunity to participate in developing this AD. We received one comment in support of the AD. The following presents the additional comments received on the proposal and FAA’s response to each comment:
Comment Issue No. 1: Incorporate Additional Lycoming Service Instructions

Gerald Stroum and Gerald Blank suggest that Lycoming Service Instructions 1448 and 1238B be incorporated into the AD because they contain helpful instructions and procedures for the proper installation of exhaust components.

Mr. Stroum also suggests that adding a requirement to free all slip joints when replacing the clamp will assist in enabling the exhaust system to be installed and aligned correctly.

The commenters state that these types of clamps (spot welded) have been used with a long history of success in the automotive diesel industry, and the issue is more readily solved by proper installation than by a change in clamp design. Their experience shows properinstallation, torque techniques, and pretorque alignments of components go a long way in preventing clamp failures down the road.

We agree with the commenters that proper installation and maintenance, which includes freeing the slip joint to ensure proper operation, plays a key role in the longevity and proper function of the exhaust system.

The data in Lycoming Service Instruction 1448 contains references to part numbers that are not the subject of this AD; therefore, we have determined including reference to that service instruction would provide confusing and contradictory information. However, we agree Lycoming Service Instruction 1238B provides beneficial information about the proper assembly and torque procedures of V-band clamps.

We will change the final rule AD action to incorporate by reference Lycoming Service Instruction 1238B. We will not change the final rule AD action to incorporate reference to Lycoming Service Instruction 1448.

Comment Issue No. 2: Correct the Cost of Compliance

Gerald Blank, Ed Novak, and Shoreline Aviation, Inc. state that the Cost of Compliance section in the proposed AD incorrectly reflects the number of V-band clamps installed on the airplanes affected by this AD.

All three commenters suggest changing the Cost of Compliance sectionto accurately reflect the number of Vband clamps installed on each affected model airplane.

We agree with the commenters. After further research, we determined that Model PA–32R–301T (Saratoga II TC) has two of the affected V–Band clamps installed, and Model PA–46–350P (Mirage) has one. We will change the final rule AD action to incorporate this change.

Comment Issue No. 3: The AD Should Be Written Against the V-Band Clamp Instead of the Airplanes

Ed Novak and Shoreline Aviation, Inc. both suggest that since identical clamps have failed on other airplane models that prompted two previous ADs (AD 2000–11–04 for Commander Aircraft Company (Commander) Model 114TC airplanes and AD 2004–23–17 for Mooney Airplane Company, Inc., (Mooney) Model M20M airplanes), this AD should be written against the Lycoming engine/clamp combination restricting its use on any exhaust system.

Shoreline Aviation, Inc. states the incident that prompted this AD would not have happened if the previous ADs had been written against the clamp and not the airplanes.

Based on the specific reports the FAA has received to date regarding Piper Aircraft, Inc. Models PA–32R–301T and PA–46–350P airplanes and with the subsequent issuance of Piper Service Bulletin 1180A, the FAA initiated this AD action against certain Piper airplanes only.

We will continue to collect and analyze all available data to determine whether the condition exists in any other airplane configurations. We may take additional rulemaking action in the future to address either additional airplane configurations or the engine design depending on the FAA’s determination of all existing and future information received.

Conclusion

We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for incorporating reference to Lycoming Service Instruction 1238B and updating the Cost of Compliance section to accurately reflect how many V-band clamps each model of the airplanes affected by this AD has installed, and 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. Costs of Compliance

We estimate that this AD affects 596 airplanes in the U.S. registry provided they have the affected V-band exhaust coupling installed.

We estimate the following costs to do the replacement for Model PA–46–350Pairplanes. These airplanes have one Vband clamp installed:


## 35621 Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations

Labor cost Parts cost Total cost per model PA–46–350P

airplane

2 work-hours × $85 per hour = $170 ............................................................................................................

.......... $714 $884



### We estimate the following costs to do the replacement for Model PA–32R– 301T airplanes. These airplanes have two V-band clamps installed:

Labor cost Parts cost Total cost per model PA–

32R–301T

airplane

2 work-hours per V-band clamp. 2 clamps per airplane: 4 work-hours × $85

per hour = $340. $714 per V-band clamp. $714 × 2 = $1,428. ..... $1,768



### 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 AD. Regulatory Findings

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.

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–2010–0122; Directorate Identifier 2009–CE–067–AD ’’ in your request. 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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. FAA amends § 39.13 by adding a new AD to read as follows: 2010–13–07 Piper Aircraft, Inc.: Amendment 39–16338; Docket No. FAA–2010–0122; Directorate Identifier 2009–CE–067–AD.

Effective Date

(a) This AD becomes effective on July 28,

2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to the following airplane models and serial numbers that are certificated in any category:

Model Serial numbers

PA–32R–301T 3257001 through 3257311. PA–46–350P .... 4622001 through 4622200 and 4636001 through 4636341.

Subject

(d) Air Transport Association of America (ATA) Code 78: Engine Exhaust.

Unsafe Condition

This AD is the result of reports that spotwelded, V-band exhaust couplings are failing. We are issuing this AD to prevent failure of the V-band exhaust coupling, which could cause the exhaust pipe to detach from the turbocharger. This failure could result in release of high-temperature gases inside the engine compartment and possibly cause an in-flight fire. An in-flight fire could lead to loss of control.
Compliance

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


## 35622 Federal Register / Vol. 75, No. 120 / Wednesday, June 23, 2010 / Rules and Regulations

Actions Compliance Procedures

(1) Replace V-band exhaust couplings, part

number (P/N) Lycoming 40D21162–340M orEaton/Aeroquip 55677–340M with an improved design Eaton/Aeroquip P/N NH1009399–10 or Lycoming P/N 40D23255– 340M. At the next regularly scheduled maintenance event after July 28, 2010 (the effective dateof this AD) or within the next 25 hours timein-service (TIS) after July 28, 2010 (the effective date of this AD), whichever occurs first. Remove the spot welded V-band clamp(s) and discard. Then, do either of the following actions: (i) Install the new riveted clamp(s) and tighten

to an initial torque of 40 in. lbs. Tap the Vband clamp(s) around its circumferencewith a rubber mallet to equalize band tension. Retorque the clamp(s) to 60 in. lbs.and again tap the clamp(s) around its circumference. Retorque the clamp(s) to a 60in. lbs. final torque and re-safety wire the Vband coupling(s); or (ii) Install the new riveted clamp(s) follow

Lycoming Service Instruction No. 1238B, dated January 6, 2010, and re-safety wire the V-band coupling(s). (2) Do not install any Eaton/Aeroquip P/N

55677–340M or Lycoming P/N 40D21162– 340M. As of July 28, 2010 (the effective date of this AD). Not applicable.

Alternative Methods of Compliance (AMOCs)

(f) The Manager, Atlanta Aircraft Certification Office (ACO), 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: Darby Mirocha, Aerospace Engineer, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474–5573; fax: (404) 474–5606. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.
Material Incorporated by Reference

(g) You must use Lycoming Service Instruction No. 1238B, dated January 6, 2010, or the procedures specified in paragraph (e)(1) of this AD 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 Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone: (570) 323–6181; fax: (570) 327–7101; Internet: http://www.lycoming.com.

(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 June 14, 2010. Sandra J. Campbell, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–14991 Filed 6–22–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0273; Directorate Identifier 2009–NM–134–AD; Amendment**  **39–16335; AD 2010–13–04]**

**RIN 2120–AA64**



### Airworthiness Directives; Bombardier, **Inc. Model DHC–8–400 Series Airplanes** 

**AGENCY** 

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

**ACTION** 

### : Final rule.

**SUMMARY** 

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

Two in-service incidents have been reported on DHC–8 Series 400 aircraft in which the nose landing gear (NLG) trailing arm pivot pin retention bolt (part number NAS6204–13D) was damaged. One incident involved the left hand NLG tire which ruptured on take-off. Investigation determined that the retention bolt failure was due to repeated contact of the castellated nut with the towing device including both the towbar and the towbarless rigs. The loss of the retention bolt allowed the pivot pin to migrate from its normal position and resulted in contact with and rupture of the tire. The loss of the pivot pin could compromise retention of the trailing arm and could result in a loss of directional control due to loss of nose wheel steering. The loss of an NLG tire or the loss of directional control could adversely affect the aircraft during take off or landing.


### * * * * *

We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective July 28, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 28, 2010.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT** 

### : Richard Beckwith, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7302; fax (516) 794–5531.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on March 23, 2010 (75 FR 13682). That NPRM proposed to correct