Document ID: FAA-2013-0602-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Vulcanair S.p.A. Airplanes
Posted Date: 2013-07-09T04:00Z

[Federal Register Volume 78, Number 131 (Tuesday, July 9, 2013)]
[Proposed Rules]
[Pages 41005-41009]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-16394]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 78, No. 131 / Tuesday, July 9, 2013 / 
Proposed Rules  

[[Page 41005]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0602; Directorate Identifier 2012-CE-010-AD]
RIN 2120-AA64

Airworthiness Directives; Vulcanair S.p.A. 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 
Vulcanair S.p.A. (type certificate previously held by Partenavia) 
Models P 68, P 68B, P 68C, P 68C-TC, P 68 ``OBSERVER,'' P68TC 
``OBSERVER,'' and P68 ``OBSERVER 2'' airplanes that would supersede AD 
2008-24-11, Amendment 39-15751. 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 cracking and/or corrosion of the wing spar, which could 
result in structural failure of the wing. We are issuing this proposed 
AD to require actions to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by August 23, 2013.

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.
    For service information identified in this proposed AD, contact 
Vulcanair Airworthiness Office, Via G Pascoli, 7, 80026 Casoria, Italy; 
phone: +39 081 59 18 135; fax: +39 081 59 18 172; email: 
airworthiness@vulcanair.com; Internet: http://www.vulcanair.com/page-view.php?pagename=Service Bulletins. You may review copies of the 
referenced service information at the FAA, Small Airplane Directorate, 
901 Locust, Kansas City, Missouri 64106. For information on the 
availability of this material at the FAA, call (816) 329-4148.

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: Mike Kiesov, Aerospace Safety 
Engineer, FAA, Small Airplane Directorate, 901 Locust, Kansas City, 
Missouri 64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: 
mike.kiesov@faa.gov.

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-2013-0602; 
Directorate Identifier 2012-CE-010-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://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

    On November 19, 2008, we issued AD 2008-24-11, Amendment 39-15751 
(73 FR 72314; November 28, 2008). That AD required actions intended to 
address an unsafe condition on the Vulcanair S.p.A. 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.
    Since we issued AD 2008-24-11 (73 FR 72314; November 28, 2008), 
Vulcanair S.p.A. developed modification kits to repair certain lower 
spar caps. They also developed a maintenance manual supplement with 
special inspections of the wing and stabilator structures and new 
limitations for the wing structure.
    The FAA also realized that the Models AP68TP300 ''SPARTACUS'' and 
AP68TP 600 ''VIATOR'' were inadvertenly included in AD 2008-24-11.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No.: 2010-0051, dated March 25, 2010 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Safe Life Limits of the wing structure of P.68 Series aeroplanes 
have now been extended up to a maximum of 23 900 Flight Hours (FH), 
depending on the condition of the spar lower cap angles and on the 
embodiment of some modification kits. Furthermore, special 
inspections of the wing and stabilator structures, different from 
those previously required by EASA AD 2007-0027, have also been 
introduced. This change has been developed by Vulcanair under change 
No. MOD. P68/144 approved by EASA with approval No. 10028661 on 02 
February 2010.
    Consequently this AD, which supersedes EASA AD 2007-0027, allows 
the implementation of the extended Safe Life Limits, in accordance 
with the instructions of Vulcanair SB 162, and requires the 
accomplishment of special inspections for the wing and stabilator 
structures, in accordance with the Aircraft Maintenance Manual (AMM) 
Supplement part number (P/N) NOR 10.771-52.

[[Page 41006]]

You may obtain further information by examining the MCAI in the AD 
docket.
    EASA AD No.: 2010-0051, dated March 25, 2010; Vulcanair S.p.A. 
Maintenance Manual Supplement NOR10.771-52, dated March 1, 2010; 
Vulcanair S.p.A. Service Bulletin No. 162, dated March 1, 2010; 
Vulcanair S.p.A. Service Instruction No. 88, dated March 1, 2010; and 
Vulcanair S.p.A. Service Instruction No. 89, dated March 1, 2010, base 
the extended safe life limits on repetitive inspections and other 
required preventive and corrective actions that under certain 
conditions allow flight with known cracks in critical structure. The 
FAA's Small Airplane Directorate does not allow further flight with 
known cracks in critical structure without additional substantiating 
data. Advisory Circular (AC) 23-13A, Chapter 6, dated September 29, 
2005, describes what additional data is required to allow flight with 
known cracks (found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf).

Relevant Service Information

    Vulcanair S.p.A. has issued Maintenance Manual Supplement 
NOR10.771-52, dated March 1, 2010; Vulcanair S.p.A. Service Bulletin 
No. 162, dated March 1, 2010; Vulcanair S.p.A. Service Instruction No. 
88, dated March 1, 2010; and Vulcanair S.p.A. Service Instruction No. 
89, dated March 1, 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 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.

Costs of Compliance

    We estimate that this proposed AD will affect 75 products of U.S. 
registry. We also estimate that it would take about 60 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $382,500, or $5,100 per product.
    We estimate that the wing replacement would take about 300 work-
hours and require parts costing $443,406, for a cost of $468,906 per 
product. Wing replacement is only required when the wing structure 
exceeds the safe life established in this AD.
    In addition, we estimate that any necessary follow-on actions for 
kit installation would take about 120 work-hours and require parts 
costing $2,595, for a cost of $12,795 per product. We have no way of 
determining the number of products that may need these 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.

Initial Regulatory Flexibility Analysis

    This section presents the initial regulatory flexibility analysis 
(IRFA) that was done for this action. We have reworded and reformatted 
for Federal Register publication purposes. The IRFA in its original 
form can be found in the docket at http://www.regulations.gov.

Introduction and Purpose of This Analysis

    The Regulatory Flexibility Act of 1980 (Pub. L. 96-354) (RFA) 
establishes ``as a principle of regulatory issuance that agencies shall 
endeavor, consistent with the objectives of the rule and of applicable 
statutes, to fit regulatory and informational requirements to the scale 
of the businesses, organizations, and governmental jurisdictions 
subject to regulation.'' To achieve this principle, the RFA requires 
agencies to solicit and consider flexible regulatory proposals and to 
explain the rationale for their actions to assure that such proposals 
are seriously considered.'' The RFA covers a wide-range of small 
entities, including small businesses, not-for-profit organizations, and 
small governmental jurisdictions.
    Agencies must perform a review to determine whether a rule will 
have a significant economic impact on a substantial number of small 
entities. If the agency determines that it will, the agency must 
prepare an IRFA as described in the RFA.
    Section 603(a) of the RFA requires that each initial regulatory 
flexibility analysis contain the following information:
     A description of the reasons action by the agency is being 
considered;
     A succinct statement of the objectives of, and legal basis 
for, the proposed rule;
     A description of and, where feasible, an estimate of the 
number of small entities to which the proposed rule will apply;
     A description of the projected reporting, recordkeeping 
and other compliance requirements of the proposed rule, including an 
estimate of the classes of small entities which will be subject to the 
requirement and the type of professional skills necessary for 
preparation of the report or record;
     To the extent practicable, an identification of all 
relevant Federal rules which may duplicate, overlap, or conflict with 
the proposed rule; and
     A description of any significant alternatives to the 
proposed rule which accomplish the stated objectives of applicable 
statues and which minimize any significant economic impact of the 
proposed rule on small entities.
    The following represents a detailed description of the six items 
required by section 603(a) of the RFA.
1. A Description of the Reasons Action by the Agency Is Being 
Considered
    This proposed AD results from mandatory continuing airworthiness 
information (MCAI) originated by EASA and would supersede AD 2008-24-
11, Amendment 39-15751 (73 FR 72314; November 28, 2008). AD 2008-24-11 
established safe limits for the wing structure of Vulcanair P 68 series 
airplanes and required repetitive inspection and repair of the wing and 
stabilator structures when the airplanes reach safe life limits. 
Operation beyond existing conservative safe limits (with inspections 
and repair) is allowed pending establishment of final safe limits and a 
terminating action.
    The proposed AD significantly increases wing structure life limits 
(in a few cases requiring kit modification of

[[Page 41007]]

the wing structure), but establishes a terminating action requiring 
replacement of the wing structure and wing fuselage attachments and 
bolts when new established safe limits are reached. Prior to the wing 
structure safe life limit being reached, the proposed AD also requires 
special inspections of the wing structure with time limits, since new, 
of 6,000; 12,000; and 18,000 flight hours.
2. Objectives of, and Legal Basis for, the Proposed Rule
    Title 49 of the U.S. 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 FAA's authority. We propose 
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 the airplanes identified in this AD.
3. A Description of and an Estimate of the Number of Small Entities to 
Which the Proposed Rule Will Apply
    This proposed rule would affect 67 U.S.-registered airplanes, of 
which 40 are owned by corporations, 8 by individuals, 2 by the Federal 
Government, and 17 by state governments. Of the 48 airplanes held by 
private sector parties, one financing firm owns 2 of them, and 2 
operators each own 2 of them. The remaining 36 airplanes are owned by 
36 corporations and individuals. The FAA believes that all, or nearly 
all, of these private sector owners are privately held small firms, for 
which we cannot obtain financial records. We conclude that the proposed 
rule would affect a substantial number of small entities.
4. Reporting, Record Keeping, and Other Compliance Requirements of the 
Proposed Rule
    Small entities will incur no new reporting and record-keeping 
requirements as a result of this rule.
    The additional requirements of the proposed AD compared to AD 2008-
24-11, Amendment 39-15751 (73 FR 72314; November 28, 2008) are the 
special wing structure inspections at 6,000; 12,000; and 18,000 flight 
hours; the terminating action to replace the wing structure when the 
wing structure safe limit is reached; and, for airplanes with serial 
numbers 1-256 for which a spar crack was found under previous 
Partenavia Costruzioni Aeronautiche S.p.A. Service Bulletin No. 65, 
Revison 3, dated September 30, 1985, replacement of the four main spar 
lower cap angles using Vulcanair S.p.A. Service Bulletin No. 162, dated 
March 1, 2010. The costs of the required actions provided in the 
proposed AD are as follows:

----------------------------------------------------------------------------------------------------------------
                                                                                      Cost of
                   Requirement                      Work-hours      Labor cost       materials      Total cost
----------------------------------------------------------------------------------------------------------------
Special inspections.............................              60          $5,100
Wing structure replacement......................             300          25,500        $443,406        $468,906
Replacement of lower spar cap angles with                    120          10,200           2,595          12,795
 Service Bulletin 162 (S/N 1-256)...............
----------------------------------------------------------------------------------------------------------------
Figure 1 of the Initial Regulatory Flexibility Analysis in this AD.

    The requirement to replace the wing structure, at considerable 
cost, occurs when the airplanes are old and have low value, often less 
than the cost of wing structure replacement. Therefore, in many cases 
airplane retirement is the least cost alternative, in which case the 
effective cost of the requirement is the loss in airplane value net of 
salvage value. The requirement to replace the lower spar cap angles 
applies to at most ten U.S.-registered airplanes and only if a front 
spar crack was previously found under Partenavia Costruzioni 
Aeronautiche S.p.A. Service Bulletin No. 65, Revison 3, dated September 
30, 1985. The expected present value cost of this requirement is thus 
minimal. The requirement for special inspections at 6,000; 12,000; and 
18,000 flight hours applies to all AD-affected airplanes.

Economic Impact on Small Entities

    Since we have no financial information of the privately held firms 
that constitute most of the operators of the affected airplanes, we 
assess the economic impact of the proposed rule using airplane values. 
As the Vulcanair P 68 airplanes are not listed in the Aircraft Bluebook 
Price Digest, we undertook an internet search and found that the resale 
value of older P 68 airplanes, manufactured between 1975 and 1984 
ranged from about $80,000 to $300,000. Many of these airplanes will be 
subject to the special inspection at 6,000 hours or even the special 
inspection at 12,000 hours. Using a significant economic impact 
criterion of 2 percent of airplane value, for operators of many of 
these airplanes there is a significant economic impact based on just 
one $5,100 inspection. Taking into account the present value cost of 
two to three possible future inspections and possible repair, as well 
as the present value cost of forced early retirement, there is a 
significant economic impact on most if not all of these operators.
    Therefore, we conclude that this proposed rule will have a 
significant impact on a substantial number of firms.
5. Duplicative, Overlapping or Conflicting Federal Rules
    The FAA is unaware of any Federal rules that duplicate, overlap, or 
conflict with this proposed rule.
6. Significant Alternatives to the Proposed Rule
    Because of an unsafe condition that is likely to exist or develop 
on the airplanes identified in this proposed AD, there is no feasible 
significant alternative to requiring the actions of this proposed AD. 
The FAA invites public comment on this determination.

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),

[[Page 41008]]

    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will have a significant economic impact, positive or negative, 
on a substantial number of small entities under the criteria of the 
Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-15751 (73 FR 
72314; November 28, 2008), and adding the following new AD:

Vulcanair S.p.A. (Type Certificate Previously Held by Partenavia): 
Docket No. FAA-2013-0602; Directorate Identifier 2012-CE-010-AD.

(a) Comments Due Date

    We must receive comments by August 23, 2013.

(b) Affected ADs

    This AD supersedes AD 2008-24-11, Amendment 39-15751 (73 FR 
72314; November 28, 2008).

(c) Applicability

    This AD applies to Vulcanair S.p.A. Models P 68, P 68B, P 68C, P 
68C-TC, P 68 ``OBSERVER,'' P68TC ``OBSERVER,'' and P68 ``OBSERVER 
2'' airplanes, serial numbers (S/N) 01 through 429, S/Ns 431 through 
452, and S/N 454, certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 57: Wings.

(e) Reason

    This AD was prompted by 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 cracking and/or 
corrosion of the wing spar. We are issuing this AD to detect and 
correct cracking and corrosion of the wing spars, which, if not 
corrected, could result in structural failure of the wing.

(f) Actions and Compliance

    Unless already done, do the following actions specified in 
paragraphs (f)(1) through (f)(8) of this AD, to include all 
subparagraphs.
    (1) Within 10 days after the effective date of this AD, 
incorporate Vulcanair S.p.A. Maintenance Manual Supplement 
NOR10.771-52, dated March 1, 2010, into the FAA-approved maintenance 
program (maintenance manual) following Vulcanair S.p.A. Service 
Bulletin No. 162, dated March 1, 2010.
    (2) Within 10 days after the effective date of this AD, 
determine the safe life limit of the wing structure as follows:
    (i) For all rows except rows (c) and (e) in table 1, of 
paragraph 1.3, of Vulcanair S.p.A. Service Bulletin No. 162, dated 
March 1, 2010, use the safe life limit specified in the appropriate 
row of the table; and
    (ii) For rows (c) and (e) in table 1, of paragraph 1.3, of 
Vulcanair S.p.A. Service Bulletin No. 162, dated March 1, 2010, 
before further flight, you must modify the wing structure following 
Vulcanair S.p.A. Service Bulletin No. 162, dated March 1, 2010. 
After modification, use the safe life limit specified in the 
appropriate row of the table.
    (3) Before reaching the life limit as determined in paragraph 
(f)(2) of this AD, before further flight, you must replace the wing 
structure and wing fuselage attachments and bolts with new ones. Do 
the replacement following Vulcanair S.p.A Maintenance Manual 
Supplement NOR10.771-52, dated March 1, 2010, as specified in the 
instructions in WORK PROCEDURE, paragraph 2 of Vulcanair S.p.A. 
Service Bulletin No. 162, dated March 1, 2010.
    (4) Do an initial inspection of the wing structure as specified 
in the instructions in paragraph 2.1 of Vulcanair S.p.A. Service 
Bulletin No. 162, dated March 1, 2010, at the applicable times as 
specified in paragraphs (f)(4)(i) and (f)(4)(ii). Repetitively 
thereafter inspect and replace the wing structure following the 
limitations in Vulcanair S.p.A. Maintenance Manual Supplement 
NOR10.771-52, dated March 1, 2010.
    (i) For aircraft that have not exceeded the safe life limit 
hours time-in-service (TIS) on the wing structure as determined in 
paragraph (f)(2) of this AD: Before accumulating 6,000 hours TIS on 
the wing structure or within 100 hours TIS after the effective date 
of this AD, whichever occurs later, follow Vulcanair S.p.A. 
Maintenance Manual Supplement NOR10.771-52, dated March 1, 2010. You 
may take unless already done credit for this inspection if inspected 
in compliance with AD 2008-24-11 (73 FR 72314; November 28, 2008); 
or
    (ii) For aircraft that have exceeded the safe life limit hours 
TIS on the wing structure as determined in paragraph (f)(2) of this 
AD: Within 100 hours TIS after the effective date of this AD, follow 
Vulcanair S.p.A. Service Bulletin No. 162, dated March 1, 2010.
    (5) Before accumulating 8,500 hours TIS since new on the 
stabilator, within 500 hours TIS after January 2, 2009 (the 
effective date of AD 2008-24-11 (73 FR 72314; November 28, 2008)), 
or within 500 hours TIS from the last inspection done in compliance 
with AD 2008-24-11, whichever occurs later, do the initial 
inspection of the stabilator following Vulcanair S.p.A. Maintenance 
Manual Supplement NOR10.771-52, paragraph 2.2, dated March 1, 2010, 
or Vulcanair S.p.A. Service Bulletin No. 120 Rev. 1, dated June 7, 
2006. Repetitively thereafter inspect the stabilator following the 
limitations in Vulcanair S.p.A. Maintenance Manual Supplement 
NOR10.771-52, dated March 1, 2010.
    (6) If any cracks are found during the inspections required in 
paragraphs (f)(4) and/or (f)(5) of this AD, before further flight, 
modify the wing structure following Vulcanair S.p.A. Service 
Bulletin No. 162, dated March 1, 2010.
    (7) For certain Model P 68 airplanes, AD 2009-24-03, Amendment 
39-16090 (74 FR 62211, November 27, 2009) requires repetitive 
inspections of the front and rear wing spars for cracks and 
modification if cracks are found. The modification terminates the 
repetitive inspections required in AD 2009-24-03 and may be done 
regardless if cracks are found. The actions of AD 2009-24-03 are 
independent of this AD action and remain in effect.
    (8) EASA AD No.: 2010-0051, dated March 25, 2010; Vulcanair 
S.p.A. Maintenance Manual Supplement NOR10.771-52, dated March 1, 
2010; Vulcanair S.p.A. Service Bulletin No. 162, dated March 1, 
2010; Vulcanair S.p.A. Service Instruction No. 88, dated March 1, 
2010; and Vulcanair S.p.A. Service Instruction No. 89, dated March 
1, 2010, base the required preventive and corrective actions on 
allowing flight with known cracks in critical structure. The FAA's 
Small Airplane Directorate does not allow further flight with known 
cracks in critical structure without additional substantiating data. 
Advisory Circular (AC) 23-13A,Chapter 6, dated September 29, 2005, 
describes what additional data is required to allow flight with 
known cracks (found on the Internet at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAdvisoryCircular.nsf).

(g) Other FAA AD Provisions

    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: Mike Kiesov, Aerospace Safety Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106; 
telephone: (816) 329-4144; fax: (816) 329-4090; email: 
mike.kiesov@faa.gov. 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.

(h) Related Information

    (1) Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2010-0051,

[[Page 41009]]

dated March 25, 2010, which may be found in the AD docket on the 
Internet at http://www.regulations.gov; Vulcanair S.p.A. Service 
Instruction No. 88, dated March 1, 2010; and Vulcanair S.p.A. 
Service Instruction No. 89, dated March 1, 2010, for related 
information.
    (2) For service information identified in this AD, contact 
Vulcanair Airworthiness Office, Via G Pascoli, 7, 80026 Casoria, 
Italy; phone: +39 081 59 18 135; fax: +39 081 59 18 172; email: 
airworthiness@vulcanair.com; Internet: http://www.vulcanair.com/page-view.php?pagename=Service-Bulletins.
    (3) You may view this service information at FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148.

    Issued in Kansas City, Missouri, on July 2, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013-16394 Filed 7-8-13; 8:45 am]
BILLING CODE 4910-13-P