55786 Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 

paragraph (o) or (p) of this AD terminates the 

requirements of this paragraph. 

New Requirements of This AD 

Revise Airworthiness Limitations Section 

(ALS) To Incorporate Limitations and 

Maintenance Tasks for Aging Systems 

Maintenance 

(o) Within 3 months after the effective date 

of this AD, revise the ALS of the Instructions 

for Continued Airworthiness (ICA) to 

incorporate Airbus A310 ALS Part 4—Aging 

Systems Maintenance, Revision 01, dated 

December 21, 2006; or Airbus A300–600 ALS 

Part 4—Aging Systems Maintenance, 

Revision 01, dated December 21, 2006; as 

applicable. For all tasks identified in Airbus 

A310 ALS Part 4—Aging Systems 

Maintenance, Revision 01; and Airbus A300– 

600 ALS Part 4—Aging Systems 

Maintenance, Revision 01; do the tasks at the 

later of the times specified in paragraphs 

(o)(1) and (o)(2) of this AD, except as 

provided by paragraph (p) of this AD. The 

repetitive inspections must be accomplished 

thereafter at the interval specified in Airbus 

A310 ALS Part 4—Aging Systems 

Maintenance, Revision 01; and Airbus A300– 

600 ALS Part 4—Aging Systems 

Maintenance, Revision 01. Doing an 

inspection required by this paragraph 

terminates the corresponding inspection 

required by paragraph (f), (g), (l), (m), or (n) 

of this AD. 

(1) At the initial compliance times 

(thresholds) specified in the applicable ALS 

Part 4—Aging Systems Maintenance, with 

the compliance times starting from the later 

of the times specified in paragraphs (o)(1)(i) 

and (o)(1)(ii) of this AD. 

(i) Since first flight of the airplane. 

(ii) Since the applicable part was new or 

refurbished if the part’s life (in flight hours, 

flight cycles, landings, or calendar time, as 

applicable) can be conclusively determined. 

(2) Within 3 months after doing the 

revision of the ALS of the ICA required by 

paragraph (o) of this AD. 

Note 7: Refer to Airbus OIT SE 999.0074/ 

05/BB, dated August 3, 2005, for additional 

information on the THSA life limits. 

Note 8: Refer to Airbus OIT SE 999.0008/ 

07/LB, dated January 16, 2007; and Airbus 

Service Information Letter (SIL) 05–008, 

Revision 1, dated February 21, 2007; for 

additional information on the THSA life 

limits and calculation method for unknown 

history of parts. 

(p) For airplanes on which any life 

limitation/maintenance task has been 

complied with in accordance with the 

requirements of paragraph (f), (g), (l), (m), or 

(n) of this AD (e.g., AD 2006–10–11 or AD 

2006–15–10), the last accomplishment of 

each limitation/task must be retained as a 

starting point for the accomplishment of each 

corresponding limitation/task interval now 

introduced in Airbus A310 ALS Part 4— 

Aging Systems Maintenance, Revision 01, 

dated December 21, 2006; and A300–600 

ALS Part 4—Aging Systems Maintenance, 

Revision 01, dated December 21, 2006; as 

applicable. Doing an inspection required by 

this paragraph terminates the corresponding 

inspection required by paragraph (f), (g), (l), 

(m), or (n) of this AD. 

(q) Except as provided by paragraph (r) of 

this AD: After accomplishing the actions 

specified in paragraphs (o) and (p) of this AD, 

no alternative inspection, inspection 

intervals, or limitations may be used. 

Alternative Methods of Compliance (AMOCs) 

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

ANM–116, Transport Airplane Directorate, 

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: Tom Stafford, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1622; fax (425) 

227–1149. 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) AMOCs approved previously in 

accordance with AD 2006–10–11 are not 

approved as AMOCs with this AD. 

(3) AMOCs approved previously in 

accordance with AD 2006–15–10 are not 

approved as AMOCs with this AD. 

Related Information 

(s) EASA airworthiness directive 2007– 

0092, dated April 10, 2007, also addresses 

the subject of this AD. 

Issued in Renton, Washington, on 

September 18, 2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–22632 Filed 9–25–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1020; Directorate 

Identifier 2008–CE–053–AD] 

RIN 2120–AA64 

Airworthiness Directives; Vulcanair 

S.p.A. Model P68 Series 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: 

The Safe Fatigue Limits (SFL) of the Wing 

Structure in the P68 Series aircraft have been 

redefined from the current 8,500 Flight Hours 

to a new value to be calculated up to a 

maximum of 17,500 Flight Hours. This has 

been developed by Vulcanair under Change 

No. MOD.P68/79 Rev. 1 and approved by 

EASA with No. EASA.A.C.02482 on 07 June 

2006. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by October 27, 2008. 

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 proposed 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: 

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: 

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–2008–1020; Directorate Identifier 

2008–CE–053–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 

mstockstill on PROD1PC66 with PROPOSALS

Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 55787 

closing date and may amend this 

proposed 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 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.: 2007– 

0027, dated February 5, 2007 (referred 

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

an unsafe condition for the specified 

products. The MCAI states: 

The Safe Fatigue Limits (SFL) of the Wing 

Structure in the P68 Series aircraft have been 

redefined from the current 8,500 Flight Hours 

to a new value to be calculated up to a 

maximum of 17,500 Flight Hours. This has 

been developed by Vulcanair under Change 

No. MOD.P68/79 Rev. 1 and approved by 

EASA with No. EASA.A.C.02482 on 07 June 

2006. 

The new Safe Fatigue Limits depend on: 

(a) Status of the modification 

(reinforcement) of the wing structure itself 

(Partenavia Service Bulletin No. 65 refers); 

and 

(b) Aircraft Flight Hours accumulated 

before the modification (reinforcement) was 

implemented. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Vulcanair S.p.A. has issued Service 

Bulletin No. 120 Rev. 1, dated June 7, 

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 

We estimate that this proposed AD 

will affect 72 products of U.S. registry. 

We also estimate that it would take 

about 80 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 $460,800, or $6,400 per 

product. 

We have no way of determining the 

number of products that may need any 

necessary follow-on actions. 

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 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: 

Vulcanair S.p.A. (Type Certificate No. 

A31EU formally held by Partenavia 

Costruzioni Aeronautiche S.p.A.): Docket 

No. FAA–2008–1020; Directorate Identifier 

2008–CE–053–AD. 

Comments Due Date 

(a) We must receive comments by October 

27, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Models P 68, P 68B, 

P 68C, P 68C–TC, P 68 ‘‘OBSERVER,’’ 

AP68TP300 ‘‘SPARTACUS,’’ P68TC 

‘‘OBSERVER,’’ AP68TP 600 ‘‘VIATOR,’’ and 

P68 ‘‘OBSERVER 2’’ airplanes; all serial 

numbers, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 51: Standard Practices/ 

Structures. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The Safe Fatigue Limits (SFL) of the Wing 

Structure in the P68 Series aircraft have been 

redefined from the current 8,500 Flight Hours 

to a new value to be calculated up to a 

maximum of 17,500 Flight Hours. This has 

been developed by Vulcanair under Change 

No. MOD.P68/79 Rev. 1 and approved by 

EASA with No. EASA.A.C.02482 on 07 June 

2006. 

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55788 Federal Register / Vol. 73, No. 188 / Friday, September 26, 2008 / Proposed Rules 

The new Safe Fatigue Limits depend on: 

(1) Status of the modification 

(reinforcement) of the wing structure itself 

(Partenavia Service Bulletin No. 65 refers); 

and 

(2) Aircraft Flight Hours accumulated 

before the modification (reinforcement) was 

implemented. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) For serial numbers 01 through 356, 

determine the safe fatigue limit of the wing 

structure following Vulcanair S.p.A. Service 

Bulletin No. 120 Rev. 1, dated June 7, 2006, 

within 8,500 hours time-in-service (TIS) 

since new or within 500 hours TIS after the 

effective date of this AD, whichever occurs 

later. 

(2) For serial numbers 01 through 356, 

inspect the wing structure and the wing to 

fuselage attachments following Vulcanair 

S.p.A. Service Bulletin No. 120 Rev. 1, dated 

June 7, 2006, within the safe fatigue limit 

determined in paragraph (f)(1) of this AD or 

within 500 hours TIS after the effective date 

of this AD, whichever occurs later. 

Repetitively thereafter inspect at intervals not 

to exceed every 500 hours TIS. 

(3) For serial numbers 357 and above, 

inspect the wing structure and the wing to 

fuselage attachments following Vulcanair 

S.p.A. Service Bulletin No. 120 Rev. 1, dated 

June 7, 2006, within 17,500 hours TIS since 

new or within 500 hours TIS after the 

effective date of this AD, whichever occurs 

later. Repetitively thereafter inspect at 

intervals not to exceed every 500 hours TIS. 

(4) For all serial numbers, inspect the 

stabilator following Vulcanair S.p.A. Service 

Bulletin No. 120 Rev. 1, dated June 7, 2006, 

within 8,500 hours TIS since new or within 

500 hours TIS after the effective date of this 

AD, whichever occurs later. Repetitively 

thereafter inspect at intervals not to exceed 

every 500 hours TIS. 

(5) If as a result of any inspection required 

by paragraphs (f)(2), (f)(3), or (f)(4) of this AD 

you find any discrepancies (for example, 

cracked or broken parts), do one of the 

following actions before further flight: 

(i) Repair the airplane following FAAapproved repair instructions obtained from 

Vulcanair S.p.A.; or 

(ii) Repair the airplane following a repair 

method approved by the FAA for this AD. 

Contact the FAA at the address in paragraph 

(g)(1) of this AD for an FAA-approved 

method. 

Note 1: For certain Model P 68 airplanes, 

AD 85–08–04 requires repetitive inspections 

of the front and rear wing spars for cracks 

with modification if cracks are found. The 

modification terminates the repetitive 

inspections required in AD 85–08–04 and 

may be done regardless if cracks are found. 

The actions of AD 85–08–08 are independent 

of this AD action and remain in effect. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

(1) The MCAI is extending the safe fatigue 

limits of the wing structure and the wing to 

fuselage attachments of certain airplanes. 

Airplanes registered in the United States did 

not have safe fatigue limits established for 

the wing structure and the wing to fuselage 

attachments. This AD is establishing safe 

fatigue limits for the wing structure and the 

wing to fuselage attachments. This AD is also 

establishing safe fatigue limits for the 

stabilator. 

(2) The MCAI requires implementation of 

safe fatigue limits into the airplane 

maintenance program (maintenance 

program). An airplane registered in the 

United States and operated under 14 CFR 

part 91 is required to have a maintenance 

program, but not necessarily following the 

airplane maintenance manual. This AD 

requires you to do specific actions of 

Vulcanair S.p.A. Service Bulletin No. 120 

Rev. 1, dated June 7, 2006, rather than 

incorporating those actions into the 

maintenance program. 

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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

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

329–4090. 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 FAAapproved 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 AD No.: 2007–0027, dated 

February 5, 2007; and Vulcanair S.p.A. 

Service Bulletin No. 120 Rev. 1, dated June 

7, 2006, for related information. 

Issued in Kansas City, Missouri, on 

September 17, 2008. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–22338 Filed 9–25–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 93 

[Docket No. FAA–2007–26470; and Notice 

No. 08–10] 

RIN 2120–AJ29 

Proposed Establishment of Special Air 

Traffic Rule, in the Vicinity of Luke 

AFB, AZ 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This rule would establish a 

Special Air Traffic Rule (SATR) in the 

vicinity of Luke Air Force Base (Luke) 

which would require general aviation 

(GA) traffic operating under visual flight 

rules (VFR) to establish communication 

with the Luke Radar Approach Control 

(RAPCON) while operating in the area 

around Luke. This action is necessary to 

address reported near midair collisions 

in the area around Luke and would help 

reduce the potential for midair 

collisions in the vicinity of Luke. 

DATES: Comments must be received on 

or before November 25, 2008. 

ADDRESSES: You may send comments 

identified by Docket Number FAA– 

2007–26470 using any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Bring 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

For more information on the 

rulemaking process, see the 

SUPPLEMENTARY INFORMATION section of 

this document. 

Privacy: We will post all comments 

we receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. 

Using the search function of our docket 

Web site, anyone can find and read the 

electronic form of all comments 

received into any of our dockets, 

mstockstill on PROD1PC66 with PROPOSALS