[Federal Register: June 2, 2009 (Volume 74, Number 104)]
[Proposed Rules]
[Page 26322-26326]
[DOCID:fr02jn09-23]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0496; Directorate Identifier 2008-NM-139-AD]
RIN 2120-AA64

Airworthiness Directives; Fokker Model F.27 Mark 050 and F.28
Mark 0100 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:

    Several incidents have been reported where an electrical burning
smell was noted in the cockpit, originating from the Electrical
Power Centre. Troubleshooting revealed a partly molten terminal,
which normally attaches a wire or bus bar to a stud of an Electrical
Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage
to the contactor stud itself was found. * * *
* * * * *
    This condition, if not corrected, could lead to further cases of
overheating of terminals and studs of Electrical Power Contactors P/
N SG02206, possibly resulting in the loss of electrical power
systems, electrical arcing and fire/smoke in the cockpit.

    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 July 2, 2009.

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:<PHONE_NUMBER>.
     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 Fokker service information identified in this proposed AD,
contact Fokker Services B.V., Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0) 252-627-350;
fax +31 (0) 252-627-211; e-mail
<EMAIL_ADDRESS>Internet http://
www.myfokkerfleet.com.
    For Goodrich service information identified in this proposed AD,
contact Goodrich Corporation, Power Systems, 1555 Corporate Woods
Parkway, Uniontown, Ohio 44685-8799; telephone<PHONE_NUMBER>; fax 330-
487-1902; e-mail<EMAIL_ADDRESS>Internet http://
www.goodrich.com/TechPubs.
    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<PHONE_NUMBER> or<PHONE_NUMBER>.

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<PHONE_NUMBER>) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax<PHONE_NUMBER>.

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-2009-0496;
Directorate Identifier 2008-NM-139-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

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2008-0091, dated May 13, 2008 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

    Several incidents have been reported where an electrical burning
smell was noted in the cockpit, originating from the Electrical
Power Centre. Troubleshooting revealed a partly molten terminal,
which normally attaches a wire or bus bar to a stud of an Electrical
Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage
to the contactor stud itself was found. Material investigation
revealed that the terminal, which was attached to the stud, was not
properly torque tightened when the incident occurred. Loss of torque
is considered to have occurred during operation, for reasons not
fully understood. Further loosening may have taken place in-service
under influence of vibration. As a result, poor contact caused
electrical arcing during which extremely high temperatures were
developed, leading to partial melting of the terminal.
    Investigation of some other burned contactors revealed evidence
(flat spring lock washer) of a fully torqued terminal/stud
connection when the overheating occurred. The exact cause for the
increase in temperature in the contactor and the terminal/stud could
not be determined. However, it could not be excluded that an
increase of the temperature inside the contactor could lead to
reduction of the reliability of the contactor stud/terminal
connection due to loss of lock washer tension. The affected
Electrical Power Contactor is used on several locations in the
electrical power system, i.e. Generator Line Contactor (GLC), Bus
Tie Contactor (BTC), Auxiliary Power Contactor (APC) and External
Power Contactor (EPC).

    This condition, if not corrected, could lead to further cases of
overheating of terminals and studs of Electrical Power Contactors P/
N SG02206, possibly resulting in the loss of electrical power
systems, electrical arcing and fire/smoke in the cockpit.
    For the reasons described above, this EASA Airworthiness
Directive (AD) requires the replacement of the current nut and
spring washer of the standard contactor P/N SG02206 with a new self-
locking nut.

    You may obtain further information by examining the MCAI in the AD
docket.

Relevant Service Information

    Goodrich Power Systems has issued Service Bulletin SG02206-24-01,
dated March 4, 2008. Fokker Services B.V. has issued the service
bulletins identified in the following table.

                       Table--Service Information
------------------------------------------------------------------------
          Service bulletin                           Date
------------------------------------------------------------------------
Fokker Service Bulletin SBF50-24-     November 6, 2003.
 030, including the drawings
 identified in the subsequent table,
 ``Table--Drawings Included in
 Fokker Service Bulletin SBF50-24-
 30''.
Fokker Service Bulletin SBF50-24-031  January 29, 2008.
Fokker Service Bulletin SBF100-24-    October 2, 2003.
 037, including Manual Change
 Notification--Maintenance
 Documentation MCNM F100-076, dated
 October 2, 2003, and including the
 drawings identified in the
 subsequent table, ``Table--Drawings
 Included in Fokker Service Bulletin
 SBF100-24-037''.
Fokker Service Bulletin SBF100-24-    January 29, 2008.
 041.
------------------------------------------------------------------------

                        Table--Drawings Included in Fokker Service Bulletin SBF50-24-030
----------------------------------------------------------------------------------------------------------------
         Fokker drawing--               Sheet--            Issue--                        Dated--
----------------------------------------------------------------------------------------------------------------
W7980-236.........................              02  H...................  August 1, 2003.
W7980-253.........................              40  BK..................  September 17, 2003.
W7980-253.........................              41  BK..................  September 17, 2003.
W7980-253.........................              42  BK..................  September 17, 2003.
W7980-253.........................              43  BK..................  September 17, 2003.
W7980-253.........................              44  BL..................  September 17, 2003.
W7980-253.........................              45  BK..................  September 17, 2003.
W7980-253.........................              46  BL..................  September 17, 2003.
W7980-253.........................              47  BK..................  September 17, 2003.
W7980-253.........................              48  BK..................  September 17, 2003.
W7980-253.........................              49  BL..................  September 17, 2003.
W7980-253.........................              50  BL..................  September 17, 2003.
W7980-253.........................              51  BL..................  September 17, 2003.
W7980-253.........................              52  BL..................  September 17, 2003.
W7980-253.........................              53  BL..................  September 17, 2003.
W7980-253.........................              54  BK..................  September 17, 2003.
W7980-253.........................              55  BL..................  September 17, 2003.
W7980-253.........................              56  BL..................  September 17, 2003.
W7980-253.........................              57  BK..................  September 17, 2003.
W7980-253.........................              58  BL..................  September 17, 2003.
W7980-253.........................              59  BK..................  September 17, 2003.
W7980-253.........................              60  BK..................  September 24, 2003.
W7980-253.........................              61  BK..................  September 24, 2003.
W7980-253.........................              62  BK..................  September 24, 2003.
W7980-253.........................              63  BL..................  September 24, 2003.
W7980-253.........................              64  BK..................  September 24, 2003.
W7980-253.........................              65  BL..................  September 24, 2003.
W7980-253.........................              66  BK..................  September 24, 2003.
----------------------------------------------------------------------------------------------------------------

                        Table--Drawings Included in Fokker Service Bulletin SBF100-24-037
----------------------------------------------------------------------------------------------------------------
         Fokker drawing--               Sheet--            Issue--                        Dated--
----------------------------------------------------------------------------------------------------------------
W43255............................              01  A...................  July 30, 2003.
W43255............................              02  Original............  July 30, 2003.
W43255............................              03  A...................  August 4, 2003.
W43255............................              04  A...................  July 30, 2003.
W43255............................              05  Original............  July 30, 2003.
W43255............................              06  A...................  July 30, 2003.
W43255............................              07  A...................  August 4, 2003.
----------------------------------------------------------------------------------------------------------------

    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 5 products of U.S. registry. We also estimate that
it would take about 8 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Required parts would cost about $5,715 per product. Where
the service information lists required parts costs that are covered
under warranty, we have assumed that there will be no charge for these
costs. As we do not control warranty coverage for affected parties,
some parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $31,775, or $6,355 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.

39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Fokker Services B.V.: Docket No. FAA-2009-0496; Directorate
Identifier 2008-NM-139-AD.

Comments Due Date

    (a) We must receive comments by July 2, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Fokker Model F.27 Mark 050 and F.28 Mark
0100 airplanes, certificated in any category, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 24:
Electrical power.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:
    Several incidents have been reported where an electrical burning
smell was noted in the cockpit, originating from the Electrical
Power Centre. Troubleshooting revealed a partly molten terminal,
which normally attaches a wire or bus bar to a stud of an Electrical
Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage
to the contactor stud itself was found. Material investigation
revealed that the terminal, which was attached to the stud, was not
properly torque tightened when the incident occurred. Loss of torque
is considered to have occurred during operation, for reasons not
fully understood. Further loosening may have taken place in-service
under influence of vibration. As a result, poor contact caused
electrical arcing during which extremely high temperatures were
developed, leading to partial melting of the terminal.
    Investigation of some other burned contactors revealed evidence
(flat spring lock washer) of a fully torqued terminal/stud
connection when the overheating occurred. The exact cause for the
increase in temperature in the contactor and the terminal/stud could
not be determined. However, it could not be excluded that an
increase of the temperature inside the contactor could lead to
reduction of the reliability of the contactor stud/terminal
connection due to loss of lock washer tension. The affected
Electrical Power Contactor is used on several locations in the
electrical power system, i.e. Generator Line Contactor (GLC), Bus
Tie Contactor (BTC), Auxiliary Power Contactor (APC) and External
Power Contactor (EPC).
    This condition, if not corrected, could lead to further cases of
overheating of terminals and studs of Electrical Power Contactors P/
N SG02206, possibly resulting in the loss of electrical power
systems, electrical arcing and fire/smoke in the cockpit.
    For the reasons described above, this EASA Airworthiness
Directive (AD) requires the replacement of the current nut and
spring washer of the standard contactor P/N SG02206 with a new self-
locking nut.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Except as provided by paragraphs (f)(2) and (f)(3) of this
AD: Within 36 months after the effective date of this AD, remove the
standard nuts and lock washers from the contactors having part
number (P/N) SG02206, install new self-locking nuts, and perform the
applicable tests on the Alternating Current Bus Transfer system, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF100-24-041 or SBF50-24-031, both dated January 29, 2008,
as applicable. If any test fails, before further flight, repair
using a method approved by either the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or EASA (or its
delegated agent).

    (2) Accomplishment of paragraph (f)(1) of this AD is not
required for Model F.28 Mark 0100 airplanes that have been modified
in service in accordance with Fokker Service Bulletin SBF100-24-037,
dated October 2, 2003. Accomplishment of Fokker Service Bulletin
SBF100-24-037, dated October 2, 2003, within the compliance time
specified in paragraph (f)(1) of this AD is considered an acceptable
method of compliance with the requirements of paragraph (f)(1) of
this AD.
    (3) Accomplishment of paragraph (f)(1) of this AD is not
required for Model F.27 Mark 050 airplanes that have been modified
during production to incorporate Fokker Engineering Change Record
(ECR) 51780, or for airplanes that have been modified in service in
accordance with Fokker Service Bulletin SBF50-24-030, dated November
6, 2003. Accomplishment of Fokker Service Bulletin SBF50-24-030,
dated November 6, 2003, within the compliance time specified in
paragraph (f)(1) of this AD is considered an acceptable method of
compliance with the requirements of paragraph (f)(1) of this AD.
    (4) As of 36 months after the effective date of this AD, no
person may install a contactor having P/N SG02206 on any airplane
unless it has been modified in accordance with Goodrich Power
Systems Service Bulletin SG02206-24-01, dated March 4, 2008.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service
information as follows: The MCAI does not include a corrective
action for airplanes on which the test required by paragraph (f)(1)
of this AD fails. This AD requires the corrective action specified
in paragraph (f)(1) of this AD.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Send information to Attn: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax<PHONE_NUMBER>. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal maintenance inspector (PMI) or principal avionics
inspector (PAI), as appropriate, or lacking a principal inspector,
your local flight Standards District Office.
    (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, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI EASA Airworthiness Directive 2008-0091, dated
May 13, 2008, and the service information listed in Tables 1, 2, and
3 of this AD for related information.

                      Table 1--Service Information
------------------------------------------------------------------------
          Service bulletin                           Date
------------------------------------------------------------------------
Fokker Service Bulletin SBF50-24-     November 6, 2003.
 030, including the drawings
 identified in Table 2 of this AD.
Fokker Service Bulletin SBF50-24-031  January 29, 2008.
Fokker Service Bulletin SBF100-24-    October 2, 2003.
 037, including Manual Change
 Notification--Maintenance
 Documentation MCNM F100-076, dated
 October 2, 2003, and including the
 drawings identified in Table 3 of
 this AD.
Fokker Service Bulletin SBF100-24-    January 29, 2008.
 041.
Goodrich Power Systems Service        March 4, 2008.
 Bulletin SG02206-24-01.
------------------------------------------------------------------------

                       Table 2--Drawings Included in Fokker Service Bulletin SBF50-24-030
----------------------------------------------------------------------------------------------------------------
         Fokker drawing--               Sheet--            Issue--                        Dated--
----------------------------------------------------------------------------------------------------------------
W7980-236.........................              02  H...................  August 1, 2003.
W7980-253.........................              40  BK..................  September 17, 2003.
W7980-253.........................              41  BK..................  September 17, 2003.
W7980-253.........................              42  BK..................  September 17, 2003.
W7980-253.........................              43  BK..................  September 17, 2003.
W7980-253.........................              44  BL..................  September 17, 2003.
W7980-253.........................              45  BK..................  September 17, 2003.
W7980-253.........................              46  BL..................  September 17, 2003.
W7980-253.........................              47  BK..................  September 17, 2003.
W7980-253.........................              48  BK..................  September 17, 2003.
W7980-253.........................              49  BL..................  September 17, 2003.
W7980-253.........................              50  BL..................  September 17, 2003.
W7980-253.........................              51  BL..................  September 17, 2003.
W7980-253.........................              52  BL..................  September 17, 2003.
W7980-253.........................              53  BL..................  September 17, 2003.
W7980-253.........................              54  BK..................  September 17, 2003.
W7980-253.........................              55  BL..................  September 17, 2003.
W7980-253.........................              56  BL..................  September 17, 2003.
W7980-253.........................              57  BK..................  September 17, 2003.
W7980-253.........................              58  BL..................  September 17, 2003.
W7980-253.........................              59  BK..................  September 17, 2003.
W7980-253.........................              60  BK..................  September 24, 2003.
W7980-253.........................              61  BK..................  September 24, 2003.
W7980-253.........................              62  BK..................  September 24, 2003.
W7980-253.........................              63  BL..................  September 24, 2003.
W7980-253.........................              64  BK..................  September 24, 2003.
W7980-253.........................              65  BL..................  September 24, 2003.
W7980-253.........................              66  BK..................  September 24, 2003.
----------------------------------------------------------------------------------------------------------------

                       Table 3--Drawings Included in Fokker Service Bulletin SBF100-24-037
----------------------------------------------------------------------------------------------------------------
         Fokker drawing--               Sheet--            Issue--                        Dated--
----------------------------------------------------------------------------------------------------------------
W43255............................              01  A...................  July 30, 2003.
W43255............................              02  Original............  July 30, 2003.
W43255............................              03  A...................  August 4, 2003.
W43255............................              04  A...................  July 30, 2003.
W43255............................              05  Original............  July 30, 2003.
W43255............................              06  A...................  July 30, 2003.
W43255............................              07  A...................  August 4, 2003.
----------------------------------------------------------------------------------------------------------------

    Issued in Renton, Washington, on May 20, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-12803 Filed 6-1-09; 8:45 am]

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