[Federal Register Volume 75, Number 49 (Monday, March 15, 2010)]
[Proposed Rules]
[Pages 12154-12158]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-5516]
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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 [email protected]; 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