
[Federal Register: June 19, 2009 (Volume 74, Number 117)]
[Proposed Rules]               
[Page 29144-29148]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19jn09-17]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0563; Directorate Identifier 2008-NM-180-AD]
RIN 2120-AA64

 
Airworthiness Directives; Fokker Model F28 Mark 0070 and 0100 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 29145]]

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:

    A recent design review has been carried out on the F28 Mark 
0070/0100 fuel system in accordance with the guidelines related to 
FAA SFAR 88 [Special Federal Aviation Regulation No. 88] (Fuel Tank 
Safety Program) and JAA [Joint Aviation Authorities] INT/POL/25/12. 
The review revealed that under certain failure conditions, prolonged 
dry running of the fuel transfer pumps may result in an ignition 
source in the centre wing fuel tank. This condition, if not 
corrected, could lead to ignition of flammable fuel vapors, 
resulting in fuel tank explosion and consequent loss of the 
airplane.
* * * * *
    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 20, 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 AlliedSignal Grimes Aerospace and Honeywell service information 
identified in this proposed AD, contact Honeywell Aerospace, Technical 
Publications and Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, 
Arizona 85072-2170; telephone 602-365-5535; fax 602-365-5577; Internet 
http://www.honeywell.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: 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-2009-0563; 
Directorate Identifier 2008-NM-180-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 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) has issued a regulation that 
is similar to SFAR 88. (The JAA is an associated body of the European 
Civil Aviation Conference (ECAC) representing the civil aviation 
regulatory authorities of a number of European States who have agreed 
to co-operate in developing and implementing common safety regulatory 
standards and procedures.) Under this regulation, the JAA stated that 
all members of the 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 proposed 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.

[[Page 29146]]

    On September 13, 1999, we issued AD 99-20-01, Amendment 39-11329 
(64 FR 51202, September 22, 1999). That AD requires actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 99-20-01, Fokker has released a new version of 
the flight warning computer (FWC) software. (AD 99-20-01 requires 
installation of an earlier version of the FWC software.) In addition, 
Fokker also released a new version of the software for the 
multifunction display unit (MFDU), which is necessary to install before 
the installation of the new version of the FWC software. The 
installation of the MFDU software depends on prior installation of a 
resistor in the thrust reverser indication and control system or 
installation of an improved thrust reverser unlock indication relay.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2008-0090, dated May 13, 2008 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    A recent design review has been carried out on the F28 Mark 
0070/0100 fuel system in accordance with the guidelines related to 
FAA SFAR 88 [Special Federal Aviation Regulation No. 88] (Fuel Tank 
Safety Program) and JAA [Joint Aviation Authorities] INT/POL/25/12. 
The review revealed that under certain failure conditions, prolonged 
dry running of the fuel transfer pumps may result in an ignition 
source in the centre wing fuel tank. This condition, if not 
corrected, could lead to ignition of flammable fuel vapors, 
resulting in fuel tank explosion and consequent loss of the 
airplane.
    To address and correct this unsafe condition, new software 
(version V13.55) has been developed for the Flight Warning Computer 
(FWC). This software update introduces a decreased time delay of the 
centre wing fuel tank low pressure alert from 15 minutes to 60 
seconds, to stop prolonged dry running of the fuel transfer pumps.
    For the reasons described above, this EASA Airworthiness 
Directive (AD) requires the replacement of the FWC with a modified 
unit, incorporating software version V13.55.

    The corrective actions also include revising the airplane flight 
manual (AFM) to change certain indications and warnings; installing new 
software for the MFDU; and installing a new resistor in the thrust 
reverser indicator and control system, or an improved thrust reverser 
unlock indication relay. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Fokker Services B.V. has issued Service Bulletins SBF100-31-067, 
Revision 1, dated April 24, 2008; SBF100-31-060, dated June 1, 2002; 
SBF100-78-016, dated October 1, 1999; SBF100-78-017, dated December 1, 
1999; and Manual Change Notification--Operational Documentation (MCNO) 
F100-050, dated January 31, 2008. Honeywell has issued Service Bulletin 
80-0610-31-0003, dated February 13, 2008. The actions described in the 
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 4 products of U.S. registry.
    The actions that are required by AD 99-20-01 and retained in this 
proposed AD take about 7 work-hours per product, at an average labor 
rate of $80 per work hour. Required parts cost about $1,593 per 
product. Based on these figures, the estimated cost of the currently 
required actions is $2,153 per product.
    We estimate that it would take about 7 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $80 per work-hour. Required parts would cost about $5,350 
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 $23,640, or $5,910 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

[[Page 29147]]

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 39-11329 (64 FR 
51202, September 22, 1999) and adding the following new AD:

Fokker Services B.V.: Docket No. FAA-2009-0563; Directorate 
Identifier 2008-NM-180-AD.

Comments Due Date

    (a) We must receive comments by July 20, 2009.

Affected ADs

    (b) The proposed AD supersedes AD 99-20-01, Amendment 39-11329.

Applicability

    (c) This AD applies to airplanes, certificated in any category, 
as identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Fokker Model F.28 Mark 0100 airplanes, all serial numbers.
    (2) Fokker Model F.28 Mark 0070 airplanes, serial numbers 11521, 
11528 through 11537 inclusive, 11545, 11547, 11553, 11557, 11561, 
11562, 11566, 11567, 11571, 11572, 11576 through 11579 inclusive, 
and 11581 through 11583 inclusive. All airplanes with these serial 
numbers are fitted with center wing fuel tanks.

Subject

    (d) Air Transport Association (ATA) of America Codes 31 and 78: 
Instruments and Engine Exhaust, respectively.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    A recent design review has been carried out on the F28 Mark 
0070/0100 fuel system in accordance with the guidelines related to 
FAA SFAR 88 [Special Federal Aviation Regulation No. 88] (Fuel Tank 
Safety Program) and JAA [Joint Aviation Authorities] INT/POL/25/12. 
The review revealed that under certain failure conditions, prolonged 
dry running of the fuel transfer pumps may result in an ignition 
source in the centre wing fuel tank. This condition, if not 
corrected, could lead to ignition of flammable fuel vapors, 
resulting in fuel tank explosion and consequent loss of the 
airplane.
    To address and correct this unsafe condition, new software 
(version V13.55) has been developed for the Flight Warning Computer 
(FWC). This software update introduces a decreased time delay of the 
centre wing fuel tank low pressure alert from 15 minutes to 60 
seconds, to stop prolonged dry running of the fuel transfer pumps.
    For the reasons described above, this EASA Airworthiness 
Directive (AD) requires the replacement of the FWC with a modified 
unit, incorporating software version V13.55.
    The corrective actions also include revising the airplane flight 
manual (AFM) to change certain indications and warnings; installing 
new software for the multifunction display unit (MFDU); and 
installing a new resistor in the thrust reverser indicator and 
control system, or an improved thrust reverser unlock indication 
relay.

Restatement of Requirements of AD 99-20-01 With No Changes to the 
Modifications

Modifications

    (f) Unless already done, within 18 months after October 27, 1999 
(the effective date of AD 99-20-01), modify the electrical wiring of 
the FWC in accordance with Part 1 or 2, as applicable, of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-31-
047, Revision 1, dated March 21, 1997.

    Note 1:  It is not necessary to install computer software 
version V10.40 into the FWC, since a later version is available and 
is required to be installed by AD 99-20-01.

    (g) Unless already done, concurrently with the accomplishment of 
the requirements of paragraph (f) of this AD, install upgraded 
computer software version V11.45 into the FWC in accordance with 
Fokker Service Bulletin SBF100-31-051, dated August 15, 1998.

    Note 2:  AlliedSignal Grimes Aerospace has issued Service 
Bulletin 80-0610-31-0031, dated May 14, 1998, as an additional 
source of service information for installation of the upgraded 
computer software version into the FWC.


    Note 3:  Operators should note that Fokker Service Bulletin 
SBF100-31-051, dated August 15, 1998, specifies prior or concurrent 
accomplishment of Fokker Service Bulletin SBF100-78-014 [which 
specifies concurrent accomplishment of Fokker Component Service 
Bulletin (CSB) P41440-78-04, and prior or concurrent accomplishment 
of Fokker Service Bulletin SBF100-78-012 and CSB P41440-78-05]. 
Related FAA AD 99-20-02, amendment 39-11330, requires accomplishment 
of these four other service bulletins.

New Requirements of This AD: Actions and Compliance

    (h) Unless already done, do the following actions.
    (1) Within 36 months after the effective date of this AD, 
replace FWC units having part number (P/N) 80-0610-3-45 and P/N 80-
0610-3-50 with modified units having P/N 80-0610-3-55, in accordance 
with the Accomplishment Instructions of Fokker Service Bulletin 
SBF100-31-067, Revision 1, dated April 24, 2008.
    (2) Within 36 months after the effective date of this AD and 
concurrently with the accomplishment of paragraph (h)(1) of this AD, 
revise the Emergency and Abnormal Procedures sections of the 
airplane flight manual (AFM), as specified in Fokker Manual Change 
Notification-Operational Documentation (MCNO) F100-050, dated 
January 31, 2008. These sections provide alterations, which are 
introduced by Fokker Service Bulletin SBF100-31-067, Revision 1, 
dated April 24, 2008.

    Note 4:  Revisions to the Emergency Procedures and Abnormal 
Procedures sections of the AFM, as specified in Fokker MCNO F100-
050, dated January 31, 2008, may be done by inserting copies of 
Fokker MCNO F100-050, dated January 31, 2008, into the AFM. When the 
information in Fokker MCNO F100-050, dated January 31, 2008, has 
been included in general revisions of the AFM, the general revisions 
may be inserted in the AFM, provided the relevant information in the 
general revision is identical to that in Fokker MCNO F100-050, dated 
January 31, 2008.

    (3) After accomplishing paragraph (h)(1) of this AD, no person 
may install an FWC having P/N 80-0610-3-45 or P/N 80-0610-3-50, 
unless it has been modified to P/N 80-0610-3-55 standard in 
accordance with Honeywell Service Bulletin 80-0610-31-0003, dated 
February 13, 2008.
    (4) Within 36 months after the effective date of this AD, 
install software version V12 for the MFDU in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-31-
060, dated June 1, 2002.
    (5) Within 36 months after the effective date of this AD, modify 
the thrust reverser indication and control system in accordance with 
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
78-016, dated October 1, 1999; or modify the thrust reverser unlock 
indication relay in accordance with the Accomplishment Instructions 
of Fokker Service Bulletin SBF100-78-017, dated December 1, 1999.

FAA AD Differences

    Note 5:  This AD differs from the MCAI and/or service 
information as follows:
    Item 1. Replacing the MFDU in accordance with Fokker Service 
Bulletin SBF100-31-060, dated June 1, 2002, is not included in the 
MCAI; however, this AD includes that action. It is necessary to 
install a new version of the MFDU software before installing the new 
version of the FWC software.
    Item 2. Modifying the thrust reverser indication and control 
system in accordance with Fokker Service Bulletin SBF100-78-016, 
dated October 1, 1999; or modifying the thrust reverser unlock 
indication relay in accordance with Fokker Service Bulletin SBF100-
78-017, dated December 1, 1999, is not included in the MCAI; 
however, this AD includes those actions. It is necessary to do one 
of those actions before installing the MFDU software.


[[Page 29148]]



Other FAA AD Provisions

    (i) 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: 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 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

    (j) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2008-0090, dated May 13, 2008, and the service information 
in Table 1 of this AD, for related information.

                                          Table 1--Related Information
----------------------------------------------------------------------------------------------------------------
              Service information--                     Revision level--                    Dated--
----------------------------------------------------------------------------------------------------------------
Fokker MCNO F100-50..............................  Original.................  January 31, 2008.
Fokker Service Bulletin SBF100-31-060............  Original.................  June 1, 2002.
Fokker Service Bulletin SBF100-31-067............  Revision 1...............  April 24, 2008.
Fokker Service Bulletin SBF100-78-016............  Original.................  October 1, 1999.
Fokker Service Bulletin SBF100-78-017............  Original.................  December 1, 1999.
Honeywell Service Bulletin 80-0610-31-0003.......  Original.................  February 13, 2008.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington, on June 11, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-14410 Filed 6-18-09; 8:45 am]

BILLING CODE 4910-13-P
