9660 Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations 

(1) The associated interval for any new task 

is to be counted from the effective date of this 

AD. 

(2) The associated interval for any revised 

task is to be counted from the previous 

performance of the task. 

(3) For Model A340 airplanes that have 

exceeded the more restrictive limitations of 

Airbus A340 Certification Maintenance 

Requirements, Document 955.3019/92, Issue 

14, Maintenance Significant Items (MSI) 

21.28.00 and 21.43.00: Do the task within 

2,500 flight hours after the previous 

accomplishment. Repeat the task thereafter at 

the applicable interval in the Airbus A340 

Certification Maintenance Requirements, 

Document 955.3019/92, Issue 14. 

(4) For Model A340 airplanes that have 

accumulated more than 2,700 flight hours 

since the last maintenance done in 

accordance with Airbus A340 Certification 

Maintenance Requirements, Document 

955.3019/92, Issue 14, MSI 28.24.00: Do the 

next task within 800 flight hours after the 

effective date of this AD. Repeat the task 

thereafter at the applicable interval in the 

Airbus A340 Certification Maintenance 

Requirements, Document 955.3019/92, Issue 

14. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(h) The European Aviation Safety Agency 

airworthiness directives 2006–0224, dated 

July 27, 2006, and 2006–0225, dated July 21, 

2006, also address the subject of this AD. 

Material Incorporated by Reference 

(i) You must use Airbus A330 Certification 

Maintenance Requirements, Document 

955.2074/93, Issue 19, dated March 22, 2006; 

or Airbus A340 Certification Maintenance 

Requirements, Document 955.3019/92, Issue 

14, dated December 19, 2005; as applicable, 

to perform the actions that are required by 

this AD, unless the AD specifies otherwise. 

The Director of the Federal Register approved 

the incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service 

information. You may review copies at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

22, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3658 Filed 3–2–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26071; Directorate 

Identifier 2006–CE–51–AD; Amendment 39–

14965; AD 2007–05–04] 

RIN 2120–AA64 

Airworthiness Directives; Mooney 

Airplane Company, Inc., (Mooney) 

Models M20M and M20R Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Mooney Airplane Company, Inc., 

Models M20M and M20R airplanes. 

This AD requires you to remove the 

upper left and upper right engine mount 

attaching hardware, cut out and remove 

the upholstery and insulation between 

the fuselage tubular frame and the 

firewall, and replace the upper left and 

upper right engine mount attaching 

hardware with the new parts kit. This 

AD results from failure of the engine 

mount attaching hardware to maintain 

torque as a result of firewall insulation 

and upholstery being compressed 

between the fuselage tubular frame and 

the firewall at the upper left and upper 

right engine mount attach points. We 

are issuing this AD to prevent the upper 

right and upper left engine mounting 

hardware from losing torque, which 

could result in a reduction in engine 

mount load carrying capability and 

could lead to engine mount failure. 

DATES: This AD becomes effective on 

April 9, 2007. 

As of April 9, 2007, 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 Mooney Airplane Company, 

Inc., 165 Al Mooney Road North, 

Kerrville, Texas 78028; telephone: (830) 

896–6000, or go to: http:// 

www.mooney.com/images/pdfs/sb-pdf/ 

m20-292a.pdf. 

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–

0001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2006–26071; Directorate Identifier 

2006–CE–51–AD. 

FOR FURTHER INFORMATION CONTACT: 

Andrew McAnaul, Aerospace Engineer, 

ASW–150 (c/o MIDO–43), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; telephone: (210) 308–

3365; fax: (210) 308–3370. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 7, 2006, 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 Mooney Airplane Company, Inc. 

Models M20M and M20R airplanes. 

This proposal was published in the 

Federal Register as a notice of proposed 

rulemaking (NPRM) on November 7, 

2006 (71 FR 65062). The NPRM 

proposed to retorque the upper left and 

upper right engine mounting hardware 

as an interim action. The NPRM also 

proposed to remove the upper left and 

upper right engine mount attaching 

hardware, cut out and remove the 

upholstery and insulation between the 

fuselage tubular frame and the firewall, 

and replace the upper left and upper 

right engine mount attaching hardware 

with the new parts kit. 

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: Jack Buster of the 

Modification and Replacement Parts 

Association (MARPA) suggests that 

paragraph (g) of the proposed action be 

amended to include the Internet 

Uniform Resource Locator (URL) 

address for the relevant service 

information. 

We agree with the commenter’s (Jack 

Buster, MARPA) recommendation. We 

added the manufacturer’s Internet URL 

address in the information on how to 

obtain the relevant service information. 

Conclusion 

Since the NPRM was published, the 

manufacturer has revised the applicable 

service bulletin to clarify the fastener 

torque requirement. The change does 

not change the intent of the required 

action and does not create any 

additional burden on the owners/ 

operators. The AD will reference the 

appropriate service information: 

Mooney Airplane Company, Inc. Service 


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Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations 9661 

Bulletin M20–292A, dated December 22, 

2006, but will give credit to anyone who 

has already done the action per the 

original service bulletin. 

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. 

Costs of Compliance 

We estimate that this AD affects 198 

airplanes in the U.S. registry. 

We estimate the following costs to 

accomplish the required modifications: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

Retorquing of the upper left and upper right engine mounting hardware: 

.5 work-hours × $80 per hour = $40.

Not Applicable ................................. $40 $7,920 

Removing insulation and upholstery material at the engine mount upper 

right and upper left attaching points, and installing engine mount attaching hardware with the new parts kit: 2 work-hours X $80 per hour 

= $160.

$20 ................................................... 180 35,640 

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–2006–26071; 

Directorate Identifier 2006–CE–51–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: 

2007–05–04 Mooney Airplane Company, 

Inc., (Mooney) Models M20M and M20R 

Airplanes: Amendment 39–14965; 

Docket No. FAA–2006–26071; 

Directorate Identifier 2006–CE–51–AD. 

Effective Date 

(a) This AD becomes effective on April 9, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Mooney Airplane 

Company, Inc., (Mooney) Model M20M 

airplanes, serial numbers 27–0317 through 

27–0355 and Model M20R airplanes, serial 

numbers 29–0290 through 29–0448, that are 

certificated in any category. 

Unsafe Condition 

(d) This AD is the result of failure of the 

engine mount attaching hardware to maintain 

torque as a result of firewall insulation and 

upholstery being compressed between the 

fuselage tubular frame and the firewall at the 

upper left and upper right engine mount 

attach points. The actions specified in this 

AD are intended to prevent the upper right 

and upper left engine mounting hardware 

from losing torque. This failure could lead to 

a reduction in engine mount load carrying 

capability and could result in engine mount 

failure. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Locate and retorque the upper left and 

upper right engine mount attaching hardware.

Within the next 25 hours time-in-service (TIS) 

after April 9, 2007 (the effective date of this 

AD).

Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 

22, 2006. 


erjones on PRODPC74 with RULES
9662 Federal Register / Vol. 72, No. 42 / Monday, March 5, 2007 / Rules and Regulations 

Actions Compliance Procedures 

(2) Replace the old engine mount attaching 

hardware by doing the following:.

(i) Remove and discard the upper left and 

upper right engine mount attaching hardware; 

(ii) Cut out and remove the upholstery and 

insulation material to allow full metal-tometal contact of the fuselage tubular 

frame to the firewall; and 

(iii) Install the new upper left and upper 

right engine mount attaching hardware 

part kits 

Within the next 100 hours time-in-service 

(TIS) after April 9, 2007 (the effective date 

of this AD).

Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 

22, 2006. 

(3) If you do the actions of paragraph (e)(2) of 

this AD before the compliance time specified 

for the action in paragraph (e)(1) of this AD, 

it terminates the requirement for the action in 

paragraph (e)(1) of this AD.

As of April 9, 2007 (the effective date of this 

AD).

Follow Mooney Airplane Company, Inc. Service Bulletin M20–292A, dated December 

22, 2006. 

(f) Compliance will be acceptable if the 

above actions are accomplished by following 

the procedures described in Mooney 

Airplane Company, Inc. Service Bulletin 

M20–292, dated September 22, 2006. You 

may take ‘‘unless already done’’ credit, and 

no further action per this AD is necessary. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Fort Worth Airplane 

Certification Office, FAA, ATTN: Andrew 

McAnaul, Aerospace Engineer, ASW–150 

(c/o MIDO–43), 10100 Reunion Place, Suite 

650, San Antonio, Texas 78216; telephone: 

(210) 308–3365; fax: (210) 308–3370, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

Related Information 

(h) None. 

Material Incorporated by Reference 

(i) You must use Mooney Airplane 

Company, Inc. Service Bulletin M20–292A, 

dated December 22, 2006, 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 the Mooney Airplane 

Company, Inc., 165 Al Mooney Road North, 

Kerrville, TX 78028, telephone: 830–896–

6000, or go to: http://www.mooney.com/ 

images/pdfs/sb-pdf/m20-292a.pdf. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or 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 

February 21, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–3575 Filed 3–2–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23871; Directorate 

Identifier 2006–NE–01–AD; Amendment 39–

14975; AD 2007–05–14] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF6–80C2 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for GE 

CF6–80C2 series turbofan engines. This 

AD requires replacing certain installed 

part number (P/N) and serial number 

(SN) cast titanium weld-repaired 

forward engine mount platforms and 

cast titanium forward mount yokes, 

with a forged titanium or a non-welded 

cast titanium part. This AD results from 

the discovery of cracks, in a weldrepaired area on a forward engine 

mount platform and a forward engine 

mount yoke, found during a fluorescent 

penetrant inspection (FPI). These parts 

were weld-repaired during manufacture. 

We are issuing this AD to prevent cracks 

in the forward engine mount platform 

and forward engine mount yoke that 

could result in possible separation of 

the engine from the airplane. 

DATES: This AD becomes effective April 

9, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

General Electric Company via Lockheed 

Martin Technology Services, 10525 

Chester Road, Suite C, Cincinnati, Ohio 

45215, telephone (513) 672–8400, fax 

(513) 672–8422. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7176; fax 

(781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CF6–80C2 series turbofan 

engines. We published the proposed AD 

in the Federal Register on December 13, 

2006 (71 FR 74873). That action 

proposed to require replacing certain 

installed part number (P/N) and serial 

number (SN) cast titanium weldrepaired forward engine mount 

platforms and cast titanium forward 

mount yokes, with a forged titanium or 

a non-welded cast titanium part. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition 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 on the plaza 

level of the Department of 

Transportation Nassif Building at the 

street address stated in ADDRESSES. 


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