Document ID: FAA-2009-0496-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Fokker Model F.27 Mark 050 and F.28 Mark 0100 Airplanes
Posted Date: 2009-06-02T04:00Z

[Federal Register: June 2, 2009 (Volume 74, Number 104)]
[Proposed Rules]               
[Page 26322-26326]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[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: (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 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 
technicalservices.fokkerservices@stork.com; 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 330-487-2007; fax 330-
487-1902; e-mail twinsburg.techpubs@goodrich.com; 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 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: 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 (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-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).

[[Page 26323]]

    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

[[Page 26324]]

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).

[[Page 26325]]

    (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 (425) 227-1149. 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.
----------------------------------------------------------------------------------------------------------------

[[Page 26326]]

                       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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