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[Federal Register: March 15, 2010 (Volume 75, Number 49)]
[Proposed Rules]               
[Page 12154-12158]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15mr10-11]                         

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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: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. 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 April 29, 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 or 425-227-1152.

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:

[[Page 12155]]

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 have lengthened the 30-day comment period for proposed ADs that 
address MCAI originated by aviation authorities of other countries to 
provide adequate time for interested parties to submit comments. The 
comment period for these proposed ADs is now typically 45 days, which 
is consistent with the comment period for domestic transport ADs.
    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

    On June 5, 2006, we issued AD 2006-12-18, Amendment 39-14644 (71 FR 
34801, June 16, 2006). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2006-12-18, we have determined that additional 
limitations for fuel tank systems and Critical Design Control 
Configuration Limitations (CDCCLs) are necessary. The European Aviation 
Safety Agency (EASA), which is the Technical Agent for the Member 
States of the European Community, has issued EASA Airworthiness 
Directive 2006-0198, dated July 11, 2006 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The 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 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, 
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.

You may obtain further information by examining the MCAI in the AD 
docket.

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    The Joint Aviation Authorities (JAA) issued a regulation that is 
similar to SFAR 88. Under that regulation, the JAA stated that all 
members of the European Civil Aviation Conference (ECAC) that hold type 
certificates for transport category airplanes are required to conduct a 
design review against explosion risks.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.

Relevant Service Information

    Bombardier has issued the temporary revisions (TRs) listed in the 
following table.

[[Page 12156]]



                                                                 AMM Temporary Revisions
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                         Bombardier temporary
               Model--                        revision--                  Dated--                                   To the AMM--
--------------------------------------------------------------------------------------------------------------------------------------------------------
SD3-60 airplanes.....................  TR360-AMM-55............  November 11, 2005.......  Bombardier SD3-60 AMM, 360/MM
                                                                                           SD3-60.
SD3-60 airplanes.....................  TR360-AMM-56............  November 11, 2005.......  Bombardier SD3-60 AMM, 360/MM
                                                                                           SD3-60.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

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.

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 $3,495 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, 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 39-14644 (71 FR 
34801, June 16, 2006) and 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 April 29, 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.


[[Page 12157]]



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, 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 amendment
        Airplane model--                 bulletin--                                 AFM--
----------------------------------------------------------------------------------------------------------------
SD3-30 airplanes...............  1/2004, dated July 13,     SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7, SBH.3.8, and
                                  2004.                      SB.3.9.
SD3-60 airplanes...............  1/2004, dated July 13,     SB.4.3, SB.4.6, and SB.4.8.
                                  2004.
SD3-60 SHERPA airplanes........  1/2004, dated July 13,     SB.5.2 or 6.2.
                                  2004.
SD3-SHERPA airplanes...........  1/2004, dated July 13,     SB.6.2 or 5.2.
                                  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 pressure 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.


                                        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.
----------------------------------------------------------------------------------------------------------------


[[Page 12158]]

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

Actions and Compliance

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 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 Shorts TRs TR360-
AMM-33, dated July 27, 2004; and TR360-AMM-34, dated July 27, 2004; 
specified in paragraph (h) of this AD. After doing this revision, 
TR360-AMM-33, dated July 27, 2004; and TR360-AMM-34, dated July 27, 
2004; required by paragraph (h) of this AD may be removed.

                                        Table 3--AMM Temporary Revisions
----------------------------------------------------------------------------------------------------------------
                                   Bombardier
            Model--                 temporary          Dated--                      To this AMM--
                                   revision--
----------------------------------------------------------------------------------------------------------------
SD3-60 airplanes..............  TR360-AMM-55....  November 11,      Bombardier SD3-60 AMM, 360/MM.
                                                   2005.
SD3-60 airplanes..............  TR360-AMM-56....  November 11,      Bombardier SD3-60 AMM, 360/MM.
                                                   2005.
----------------------------------------------------------------------------------------------------------------


    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 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 March 4, 2010.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-5516 Filed 3-12-10; 8:45 am]
BILLING CODE 4910-13-P
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