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[Federal Register: August 4, 2010 (Volume 75, Number 149)]
[Proposed Rules]               
[Page 46864-46868]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04au10-11]                         

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0225; Directorate Identifier 2009-NM-203-AD]
RIN 2120-AA64

 
Airworthiness Directives; Short Brothers PLC Model SD3 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier NPRM for the products listed above. 
This action revises the earlier NPRM by expanding the scope. 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:

    Subsequent to accidents involving Fuel Tank System explosions in 
flight * * * and on ground, * * * Special Federal Aviation 
Regulation 88 (SFAR88) * * * required a safety review of the 
aircraft Fuel Tank System * * *.
* * * * *
    Fuel Airworthiness Limitations are items arising from a systems 
safety analysis that have been shown to have failure mode(s) 
associated with an `unsafe condition' * * *. These are identified in 
Failure Conditions for which an unacceptable probability of ignition 
risk could exist if specific tasks and/or practices are not 
performed in accordance with the manufacturers' requirements.
* * * * *

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 August 30, 2010.

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 W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Short Brothers PLC, Airworthiness, P.O. Box 241, Airport Road, Belfast, 
BT3 9DZ Northern Ireland; telephone +44(0)2890-462469; fax +44(0)2890-
468444; e-mail michael.mulholland@aero.bombardier.com; Internet http://www.bombardier.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
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 Operations 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: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; fax (425) 227-1149.

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-2010-0225; 
Directorate Identifier 2009-NM-203-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 based on 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

    We proposed to amend 14 CFR part 39 with an earlier NPRM for the 
specified products, which was published in the Federal Register on 
March 15, 2010 (75 FR 12154). That earlier NPRM proposed to supersede 
AD 2006-12-18, Amendment 39-14644 (71 FR 34801, June 16, 2006), to 
require actions intended to address the unsafe condition for the 
products listed above. Since that NPRM was issued, we have determined 
that the original NPRM did not include all the relevant service 
information for the affected airplanes.

Relevant Service Information

    Bombardier has issued the temporary revisions (TRs) listed in the 
following table.

[[Page 46865]]

                                                             Table--AMM Temporary Revisions
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                          Shorts temporary
               Model--                       revision--                           Dated--                          To the maintenance manual (MM)--
--------------------------------------------------------------------------------------------------------------------------------------------------------
SD3-30 airplanes....................  TR330-AMM-35...........  June 6, 2006................................  Shorts SD3-30 MM.
SD3-30 airplanes....................  TR330-AMM-36...........  June 6, 2006................................  Shorts SD3-30 MM.
SD3-SHERPA airplanes................  TRSD3S-AMM-36..........  June 19, 2006...............................  Shorts SD3[dash]SHERPA MM.
SD3-SHERPA airplanes................  TRSD3S-AMM-37..........  June 19, 2006...............................  Shorts SD3[dash]SHERPA MM.
SD3-60 SHERPA airplanes.............  TRSD360S-AMM-35........  June 27, 2006...............................  Shorts SD3-60 Sherpa MM.
SD3-60 SHERPA airplanes.............  TRSD360S-AMM-36........  June 27, 2006...............................  Shorts SD3-60 Sherpa MM.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

Comments

    We have considered the following comments received on the earlier 
NPRM.

Request To Include Additional Service Information

    Bombardier requests that we add the TRs specified in the previous 
table to Table 3 of the NPRM.
    We agree and have revised this supplemental NPRM accordingly.

Request To Revise Costs of Compliance

    Bombardier requests that we revise the costs of compliance to 
account for any Model SD3-30 airplanes.
    We agree that clarification may be necessary. The Costs of 
Compliance section accounts for 54 U.S.-registered airplanes, all of 
which are operated as transport category airplanes, not military 
airplanes.

Request To Remove Reference to Fuselage Pressure Shell

    Bombardier requests that we revise paragraph (h) of the NPRM to 
remove reference to ``longitudinal skin joints in the fuselage pressure 
shell.'' Bombardier notes that this statement is erroneous because the 
Model SD3 airplanes are not pressurized.
    We agree with the request and have removed ``pressure'' from the 
statement from paragraph (h) of this supplemental NPRM.

FAA's Determination and Requirements of This 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 the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    Certain changes described above expand the scope of the earlier 
NPRM. As a result, we have determined that it is necessary to reopen 
the comment period to provide additional opportunity for the public to 
comment on this proposed AD.

Differences Between This 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 54 products of U.S. registry.
    The actions that are required by AD 2006-12-18 and retained in this 
proposed AD take about 41 work-hours per product, at an average labor 
rate of $85 per work hour. Required parts cost about $10 per product. 
Based on these figures, the estimated cost of the currently required 
actions is $3,485 per product.
    We estimate that it would take about 1 work-hour per product to 
comply with the new 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 $4,590, or $85 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 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, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator,

[[Page 46866]]

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 adding the following new AD:

Short Brothers PLC: Docket No. FAA-2010-0225; Directorate Identifier 
2009-NM-203-AD.

Comments Due Date

    (a) We must receive comments by August 30, 2010.

Affected ADs

    (b) This AD supersedes AD 2006-12-18, Amendment 39-14644.

Applicability

    (c) This AD applies to all Short Brothers PLC Model SD3-60 
SHERPA, SD3-SHERPA, SD3-30, and SD3-60 airplanes, certificated in 
any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (l) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued damage tolerance of the affected structure. The FAA 
has provided guidance for this determination in Advisory Circular 
(AC) 25-1529.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Subsequent to accidents involving Fuel Tank System explosions in 
flight * * * and on ground, the FAA published Special Federal 
Aviation Regulation 88 (SFAR88) in June 2001. SFAR 88 required a 
safety review of the aircraft Fuel Tank System to determine that the 
design meets the requirements of FAR [Federal Aviation Regulation] 
Sec.  25.901 and Sec.  25.981(a) and (b).
    A similar regulation has been recommended by the JAA [Joint 
Aviation Authorities] to the European National Aviation Authorities 
in JAA letter 04/00/02/07/03-L024 of 3 February 2003. The review was 
requested to be mandated by NAA's [National Airworthiness 
Authorities] using JAR [Joint Aviation Requirement] Sec.  25.901(c), 
Sec.  25.1309.
    In August 2005 EASA [European Aviation Safety Agency] published 
a policy statement on the process for developing instructions for 
maintenance and inspection of Fuel Tank System ignition source 
prevention (EASA D 2005/CPRO, http://www.easa.eu.int/home/cert_policy_statements_en.html) that also included the EASA 
expectations with regard to compliance times of the corrective 
actions on the unsafe and the not unsafe part of the harmonised 
design review results. On a global scale the TC [type certificate] 
holders committed themselves to the EASA published compliance dates 
(see EASA policy statement). The EASA policy statement has been 
revised in March 2006: The date of 31-12-2005 for the unsafe related 
actions has now been set at 01-07-2006.
    Fuel Airworthiness Limitations are items arising from a systems 
safety analysis that have been shown to have failure mode(s) 
associated with an `unsafe condition' as defined in FAA's memo 2003-
112-15 `SFAR 88--Mandatory Action Decision Criteria'. These are 
identified in Failure Conditions for which an unacceptable 
probability of ignition risk could exist if specific tasks and/or 
practices are not performed in accordance with the manufacturers' 
requirements.
    This EASA Airworthiness Directive mandates the Fuel System 
Airworthiness Limitations, comprising maintenance/inspection tasks 
and Critical Design Control Configuration Limitations (CDCCL) for 
the type of aircraft, that resulted from the design reviews and the 
JAA recommendation and EASA policy statement mentioned above.
    Revision History: PAD [proposed airworthiness directive] 06-
018R1 has been issued to endorse comments received for PAD 06-018 
and due to the change of the EASA policy statement on fuel tank 
safety on March 2006.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2006-12-18, With Revised Service 
Information

Revision of Airplane Flight Manual (AFM) With Additional AFM References 
in Table 1 of This AD

    (g) Within 30 days after July 21, 2006 (the effective date of AD 
2006-12-18), revise the Limitations and Normal Procedures sections 
of the AFMs as specified in Table 1 of this AD to include the 
information in the applicable Shorts advance amendment bulletins as 
specified in Table 1 of this AD. The advance amendment bulletins 
address operation during icing conditions and fuel system failures. 
Thereafter, operate the airplane according to the limitations and 
procedures in the applicable advance amendment bulletin.

    Note 2: The requirements of paragraph (g) of this AD may be done 
by inserting a copy of the applicable advance amendment bulletin 
into the AFM. When the applicable advance amendment bulletin has 
been included in general revisions of the AFM, the general revisions 
may be inserted into the AFM and the advance amendment bulletin may 
be removed, provided the relevant information in the general 
revision is identical to that in the advance amendment bulletin.

                                             Table 1--AFM Revisions
----------------------------------------------------------------------------------------------------------------
                                     Shorts Advance
        Airplane Model--          Amendment Bulletin--                           AFM--

----------------------------------------------------------------------------------------------------------------
SD3-30 airplanes................  1/2004, dated July   SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7, SBH.3.8, and SB.3.9.
                                   13, 2004.
SD3-60 airplanes................  1/2004, dated July   SB.4.3, SB.4.6, and SB.4.8.
                                   13, 2004.
SD3-60 SHERPA airplanes.........  1/2004, dated July   SB.5.2 or 6.2.
                                   13, 2004.
SD3-SHERPA airplanes............  1/2004, dated July   SB.6.2 or 5.2.
                                   13, 2004.
----------------------------------------------------------------------------------------------------------------

Revision of Airworthiness Limitation (AWL) Section

    (h) Within 180 days after July 21, 2006: Revise the AWL section 
of the Instructions for Continued Airworthiness by incorporating 
airplane maintenance manual (AMM) Sections 5-20-01 and 5-20-02 as 
introduced by the Shorts temporary revisions (TR) specified in Table 
2 of this AD into the AWL section of the AMMs for the airplane 
models specified in Table 2 of this AD, except as required by 
paragraph (j) of this AD. Thereafter, except as provided by 
paragraph (l)(1) of this AD, no alternative structural inspection 
intervals may be approved for the longitudinal skin joints in the 
fuselage shell.

    Note 3: The requirements of paragraph (h) of this AD may be done 
by inserting a copy of the applicable TR into the applicable AMM. 
When the TR has been included in general revisions of the AMM, the 
general revisions may be inserted in the AMM and the TR may be 
removed, provided the relevant information in the general revision 
is identical to that in the TR.

[[Page 46867]]

                                        Table 2--AMM Temporary Revisions
----------------------------------------------------------------------------------------------------------------
                                   Temporary revision--
         Airplane model--                                      Dated--                       AMM--
----------------------------------------------------------------------------------------------------------------
SD3-30 airplanes.................  TR330-AMM-13........  June 21, 2004......  SD3-30 AMM.
SD3-30 airplanes.................  TR330-AMM-14........  June 21, 2004......  SD3-30 AMM.
SD3-60 airplanes.................  TR360-AMM-33........  July 27, 2004......  SD3-60 AMM.
SD3-60 airplanes.................  TR360-AMM-34........  July 27, 2004......  SD3-60 AMM.
SD3-60 SHERPA airplanes..........  TRSD360S-AMM-14.....  July 29, 2004......  SD3-60 SHERPA AMM.
SD3-60 SHERPA airplanes..........  TRSD360S-AMM-15.....  July 29, 2004......  SD3-60 SHERPA AMM.
SD3-SHERPA airplanes.............  TRSD3S-AMM-15.......  July 28, 2004......  SD3 SHERPA AMM.
SD3-SHERPA airplanes.............  TRSD3S-AMM-16.......  July 28, 2004......  SD3 SHERPA AMM.
----------------------------------------------------------------------------------------------------------------

Resistance Check, Inspection, and Jumper Installation

    (i) Within 180 days after July 21, 2006: Perform the insulation 
resistance check, general visual inspections, and bonding jumper 
wire installations; in accordance with Shorts Service Bulletin 
SD330-28-37, SD360-28-23, SD360 SHERPA-28-3, or SD3 SHERPA-28-2; all 
dated June 2004; as applicable. If any defect or damage is 
discovered during any inspection or check required by this AD, 
before further flight, repair the defect or damage using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; the Civil Aviation Authority (CAA) (or 
its delegated agent); or EASA (or its delegated agent).

    Note 4: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

New Requirements of This AD

Revision of AWL Section: New Limitations and CDCCLs

    (j) Within 90 days after the effective date of this AD: Revise 
the AWL section of the Instructions for Continued Airworthiness by 
incorporating aircraft maintenance manual (AMM) Sections 5-20-01 and 
5-20-02 as introduced by the Bombardier and Shorts temporary 
revisions (TRs) specified in Table 3 of this AD into the AWL section 
of the AMMs for the airplane models specified in Table 3 of this AD. 
Doing this revision terminates the requirement to incorporate the 
temporary revisions specified in paragraph (h) of this AD. After 
doing this revision the temporary revisions required by paragraph 
(h) of this AD may be removed.

                                                            Table 3--AMM Temporary Revisions
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Model--                   Temporary revision --            Dated--                                  To this AMM--
--------------------------------------------------------------------------------------------------------------------------------------------------------
SD3-30 airplanes.....................  Shorts TR TR330-AMM-35..  June 6, 2006............  Shorts SD3-30 Maintenance Manual (MM).
SD3-30 airplanes.....................  Shorts TR TR330-AMM-36..  June 6, 2006............  Shorts SD3-30 MM.
SD3-60 airplanes.....................  Bombardier TR TR360-AMM-  November 11, 2005.......  Bombardier SD3-60 AMM.
                                        55.
SD3-60 airplanes.....................  Bombardier TR TR360-AMM-  November 11, 2005.......  Bombardier SD3-60 AMM.
                                        56.
SD3-60 SHERPA airplanes..............  Shorts TR TRSD360S-AMM-   June 27, 2006...........  Shorts SD3-60 Sherpa MM.
                                        35.
SD3-60 SHERPA airplanes..............  Shorts TR TRSD360S-AMM-   June 27, 2006...........  Shorts SD3-60 Sherpa MM.
                                        36.
SD3-SHERPA airplanes.................  Shorts TR TRSD3S-AMM-36.  June 19, 2006...........  Shorts SD3-SHERPA MM.
SD3-SHERPA airplanes.................  Shorts TR TRSD3S-AMM-37.  June 19, 2006...........  Shorts SD3-SHERPA MM.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    Note 5: The requirements of paragraph (j) of this AD may be done 
by inserting a copy of the applicable TR into the applicable AMM. 
When the TR has been included in general revisions of the AMM, the 
general revisions may be inserted in the AMM and the TR may be 
removed, provided the relevant information in the general revision 
is identical to that in the TR.

    (k) After accomplishing the actions specified in paragraph (j) 
of this AD, no alternative inspections, inspection intervals, or 
CDCCLs may be used unless the inspections, intervals, or CDCCLs are 
approved as an alternative method of compliance (AMOC), in 
accordance with the procedures specified in paragraph (l) of this 
AD.

Explanation of CDCCL Requirements

    Note 6:  Notwithstanding any other maintenance or operational 
requirements, components that have been identified as airworthy or 
installed on the affected airplanes before the revision of the AMM, 
as required by paragraph (h) or (j) of this AD, do not need to be 
reworked in accordance with the CDCCLs. However, once the AMM has 
been revised, future maintenance actions on these components must be 
done in accordance with the CDCCLs.

FAA AD Differences

    Note 7: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (l) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): 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: Todd 
Thompson, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (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

[[Page 46868]]

Management and Budget (OMB) has approved the information collection 
requirements and has assigned OMB Control Number 2120-0056.

Related Information

    (m) Refer to MCAI EASA Airworthiness Directive 2006-0198, dated 
July 11, 2006; Shorts Service Bulletins SD330-28-37, SD360-28-23, 
SD360 SHERPA-28-3, and SD3 SHERPA-28-2, all dated June 2004; and the 
service information listed in Tables 1, 2, and 3 of this AD; for 
related information.

    Issued in Renton, Washington, on July 26, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-19172 Filed 8-3-10; 8:45 am]
BILLING CODE 4910-13-P
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