20298 Federal Register / Vol. 72, No. 78 / Tuesday April 24, 2007 / Proposed Rules 

Comments Due Date 

(a) We must receive comments by May 24, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to DA 42 airplanes, 

serial numbers (S/N) 42.004 and up, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

It has been determined that the surface 

roughness of the wing stub safety walks 

Series 300, gray color (equals sandpaper grid 

40), installed during production on some 

aeroplane S/Ns, adversely affects the aircraft 

single engine climb performance. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) For S/N 42.004 through 42.035, and 

42.037: Within 60 days after the effective 

date of this AD, do the following actions 

following Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB–42–

006/1, dated September 20, 2005: 

(i) Exchange the wing stub safety walks 

following paragraph 1.8, Action 2 a) to b) of 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB–42–

006/1, dated September 20, 2005. 

(ii) Insert Diamond Aircraft Airplane Flight 

Manual Temporary Revision Performance 

Data DA 42 AFM TR–MA ̈ M–42–111/a, dated 

September 20, 2005, Revision 3 to the 

Airplane Flight Manual (AFM), or any future 

revision that incorporates the same 

information into the Diamond Aircraft 

Industries GmbH Aircraft Airplane Flight 

Manual DA 42, Doc. 7.01.05–E. 

(2) For S/N 42.036, 42.038 through 42.064, 

42.107, 42.109, 42.110, and 42.177: Within 

60 days after the effective date of this AD, 

insert Diamond Aircraft Airplane Flight 

Manual Temporary Revision Performance 

Data DA 42 AFM TR–MA ̈ M–42–111/a, dated 

September 20, 2005, Revision 3 to the AFM, 

or any future revision that incorporates the 

same information into the Diamond Aircraft 

Industries GmbH Aircraft Airplane Flight 

Manual DA 42, Doc. 7.01.05–E. 

(3) For S/N 42.004 and up: Within 60 days 

after the effective date of this AD, adhere to 

the following: 

(i) No wing stub safety walks Series 300 

(equals sandpaper grid 40), gray color, part 

number (P/N) D60–1127–10–51 (no revision 

letter attached) may be installed as a spare 

part on the Model DA 42 airplane. Only 

Diamond Aircraft Industries (DAI) GmbH 

released safety walk P/Ns with a surface 

roughness equal to or finer than sandpaper 

grid 100 are approved for installation as 

spare parts. 

(ii) Diamond Aircraft Airplane Flight 

Manual Temporary Revision Performance 

Data DA 42 AFM TR–MA ̈ M–42–111/a, dated 

September 20, 2005, Revision 3 to the AFM, 

or any future revision that incorporates the 

same information, must remain part of 

Diamond Aircraft Industries GmbH Aircraft 

Airplane Flight Manual DA 42, Doc. 7.01.05–

E. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(1) The MCAI and service bulletin require 

the insertion of Diamond Aircraft Airplane 

Flight Manual Temporary Revision 

Performance Data DA 42 AFM TR–MA ̈ M–42–

111/a, dated September 20, 2005, Revision 3 

to the Airplane Flight Manual, or any future 

revision that incorporates the same 

information into the Diamond Aircraft 

Industries GmbH Aircraft Airplane Flight 

Manual DA 42, Doc. 7.01.05–E, immediately 

upon receipt. We consider immediately upon 

receipt as an urgent safety of flight 

compliance time, and we do not consider this 

unsafe condition to be an urgent safety of 

flight condition. Because we do not consider 

this unsafe condition to be an urgent safety 

of flight condition, we issued this action 

through the normal notice of proposed 

rulemaking (NPRM) AD process. The time of 

60 days after the effective date of this AD is 

an adequate compliance for this AD action 

and met the FAA requirements of an NPRM 

followed by a final rule. 

(2) Paragraphs A)i) and B)i) of the MCAI, 

state to assure that AFM TR–MAM–42–103, 

distributed with DAI MSB42–005, is inserted 

into AFM Doc. 7.01.05–E, rev. 2 or earlier 

revision. This AFM requirement was for an 

MCAI that the United States did not take AD 

action on. The action is no longer necessary 

when the actions proposed in this NPRM are 

done. Therefore, the action is not being 

mandated in the U.S. AD action. 

(3) The MCAI references revision 2 of the 

AFM. However, the current revision level of 

the AFM is revision 3. The FAA AD 

references revision 3. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 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. 

(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. 

(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 Austrian Civil Aviation 

Administration Austro Control GmbH AD 

No. A–2005–003, dated October 21, 2005; 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin No. MSB–42–

006/1, dated September 20, 2005; and 

Diamond Aircraft Temporary Revision 

Performance Data DA 42 AFM TR–MA ̈ M–42–

111/a, dated September 20, 2005, for related 

information. 

Issued in Kansas City, Missouri, on April 

17, 2007. 

Charles L. Smalley, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7752 Filed 4–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27723; Directorate 

Identifier 2007–CE–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; PIAGGIO 

AERO INDUSTRIES S.p.A. Model P–180 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

EASA EAD 2006–0072–E was issued on 

31st March 2006 following a further failure 

of the forward support of the Main Wing 

Outboard Flap (MWOF), caused by corrosion. 

This condition, if not corrected, may cause 

surface twisting during deployment at 

landing. The analysis of that event 

highlighted the need for the reduction of the 

previous inspection interval which was 

mandated by ENAC through AD 2004–523, 

approved by EASA with reference 2004–

12521. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 


jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 72, No. 78 / Tuesday April 24, 2007 / Proposed Rules 20299 

DATES: We must receive comments on 

this proposed AD by May 24, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

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

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

proposed AD, the regulatory evaluation, 

any comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Mr. 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4145; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–27723; Directorate Identifier 

2007–CE–029–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No. 2006–

0305, dated October 9, 2006 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

EASA EAD 2006–0072–E was issued on 

31st March 2006 following a further failure 

of the forward support of the Main Wing 

Outboard Flap (MWOF), caused by corrosion. 

This condition, if not corrected, may cause 

surface twisting during deployment at 

landing. The analysis of that event 

highlighted the need for the reduction of the 

previous inspection interval which was 

mandated by ENAC through AD 2004–523, 

approved by EASA with reference 2004–

12521. 

Now the TC holder has developed a new 

type of forward support for the Main Wing 

Outboard Flap with characteristics that 

improve the resistance to corrosion. When 

the new support is installed, the repetitive 

Eddy current inspection that was introduced 

by EASA EAD 2006–0072–E is no longer 

required. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Piaggio Aero Industries S.p.A. has 

issued Mandatory Service Bulletin No. 

80–0210, Rev. 4, dated July 19, 2006. 

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 Proposed 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 proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed 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 also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 7 products of U.S. registry. 

We also estimate that it would take 

about 16 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $80 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $8,960, or $1,280 per 

product. 

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 


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20300 Federal Register / Vol. 72, No. 78 / Tuesday April 24, 2007 / Proposed Rules 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Piaggio Aero Industries S.p.A.: Docket No. 

FAA–2007–27723; Directorate Identifier 

2007–CE–029–AD. 

Comments Due Date 

(a) We must receive comments by May 24, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model P–180 

airplanes, serial numbers 1002, 1004 through 

1107, 1109, and 1110, certificated in any 

category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

EASA EAD 2006–0072–E was issued on 

31st March 2006 following a further failure 

of the forward support of the Main Wing 

Outboard Flap (MWOF), caused by corrosion. 

This condition, if not corrected, may cause 

surface twisting during deployment at 

landing. The analysis of that event 

highlighted the need for the reduction of the 

previous inspection interval which was 

mandated by ENAC through AD 2004–523, 

approved by EASA with reference 2004–

12521. 

Now the TC holder has developed a new 

type of forward support for the Main Wing 

Outboard Flap with characteristics that 

improve the resistance to corrosion. When 

the new support is installed, the repetitive 

Eddy current inspection that was introduced 

by EASA EAD 2006–0072–E is no longer 

required. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 200 hours time-inservice (TIS) or 60 days after the effective 

date of this AD, whichever occurs first, 

replace the outboard flap track forward 

bushing and the outboard flap track forward 

support. Do the replacements using the 

Accomplishment Instructions detailed in Part 

A of Piaggio Aero Industries S.p.A. 

Mandatory Service Bulletin (SB) No. 80–

0210, Rev 4, dated July 19, 2006. 

(2) At intervals not to exceed 1,500 hours 

TIS after doing the replacements required in 

paragraph (f)(1) of this AD, visually inspect 

the outboard flap track forward support for 

traces of any kind of corrosion and/or 

protective coat/finishing wear damage. Do 

the inspections using the Accomplishment 

Instructions detailed in Part B of Piaggio 

Aero Industries S.p.A. Mandatory SB No. 80–

0210, Rev 4, dated July 19, 2006. 

(3) Before further flight after each 

inspection required in paragraph (f)(2) of this 

AD in which any kind of corrosion or wear 

damage is found, contact the manufacturer 

for a repair scheme and incorporate the 

repair. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, Small Airplane Directorate, ATTN: 

Sarjapur Nagarajan, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 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. 

(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. 

(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 European Aviation 

Safety Agency (EASA) AD No. 2006–0305, 

dated October 9, 2006; and Piaggio Aero 

Industries S.p.A. Mandatory Service Bulletin 

No. 80–0210, Rev 4, dated July 19, 2006, for 

related information. 

Issued in Kansas City, Missouri, on April 

17, 2007. 

Charles L. Smalley, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7754 Filed 4–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27432; Directorate 

Identifier 2007–CE–017–AD] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA—

Groupe AEROSPATIALE Model TB 9, 

TB 10, and TB 200 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

* * * a new life limit for engine and Nose 

Landing Gear (NLG) mounts installed on 

EADS SOCATA TB 9, TB 10 and TB 200 

airplanes, as defined in the updated 

Airworthiness Limitations Section (ALS) of 

the relevant Aircraft Maintenance Manuals 

(AMM). 


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