
[Federal Register: September 9, 2009 (Volume 74, Number 173)]
[Rules and Regulations]               
[Page 46319-46322]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09se09-7]                         

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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; 
Amendment 39-16005; AD 2009-18-09]
RIN 2120-AA64

 
Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. This 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 
aircraft.
* * * * *
    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective October 14, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 14, 
2009.
    On October 27, 1999 (64 FR 51202, September 22, 1999), the Director 
of the Federal Register approved the incorporation by reference of 
certain other publications listed in this AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 19, 2009 (74 FR 
29144), and proposed to supersede AD 99-20-01, Amendment 39-11329 (64 
FR 51202, September 22, 1999). That NPRM proposed 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 
aircraft.
    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 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. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a note within the AD.

[[Page 46320]]

Costs of Compliance

    We estimate that this AD affects about 4 products of U.S. registry.
    The actions that are required by AD 99-20-01 and retained in this 
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 takes about 7 work-hours per product to comply 
with the new basic requirements of this AD. The average labor rate is 
$80 per work-hour. Required parts 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 this AD to 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    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 AD and placed it in the AD docket.

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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-11329 (64 FR 
51202, September 22, 1999) and adding the following new AD:

2009-18-09 Fokker Services B.V.: Amendment 39-16005. Docket No. FAA-
2009-0563; Directorate Identifier 2008-NM-180-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
14, 2009.

Affected ADs

    (b) This 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 
aircraft.
    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 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

    (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

[[Page 46321]]

of guidance 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, which is included in Fokker Service Bulletin SBF100-31-
067, Revision 1, dated April 24, 2008. These AFM sections provide 
alterations, which are introduced in 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 revisions are 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:
    (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.
    (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.

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 
identified in Table 1 of this AD, for related information.

                                          Table 1--Related Information
----------------------------------------------------------------------------------------------------------------
          Service information--                 Revision level--                        Dated--
----------------------------------------------------------------------------------------------------------------
Fokker Service Bulletin SBF100-31-047...  1..........................  March 21, 1997.
Fokker Service Bulletin SBF100-31-051...  Original...................  August 15, 1998.
Fokker Service Bulletin SBF100-31-060...  Original...................  June 1, 2002.
Fokker Service Bulletin SBF100-31-067,    1..........................  April 24, 2008.
 including Fokker Manual Change
 Notification-Operational Documentation
 MCNO-F100-50, dated January 31, 2008.
Fokker Service Bulletin SBF100-78-016...  Original...................  October 1, 1999.
Fokker Service Bulletin SBF100-78-017...  Original...................  December 1, 1999.
----------------------------------------------------------------------------------------------------------------

Material Incorporated by Reference

    (k) You must use the service information contained in Table 2 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.

                                 Table 2--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                Document                            Revision                              Date
----------------------------------------------------------------------------------------------------------------
Fokker Service Bulletin SBF100-31-047...  1..........................  March 21, 1997.
Fokker Service Bulletin SBF100-31-051...  Original...................  August 15, 1998.

[[Page 46322]]


Fokker Service Bulletin SBF100-31-060...  Original...................  June 1, 2002.
Fokker Service Bulletin SBF100-31-067,    1..........................  April 24, 2008.
 including Fokker Manual Change
 Notification-Operational Documentation
 MCNO-F100-50, dated January 31, 2008.
Fokker Service Bulletin SBF100-78-016...  Original...................  October 1, 1999.
Fokker Service Bulletin SBF100-78-017...  Original...................  December 1, 1999.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

                                 Table 3--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                Document                            Revision                              Date
----------------------------------------------------------------------------------------------------------------
Fokker Service Bulletin SBF100-31-060...  Original...................  June 1, 2002.
Fokker Service Bulletin SBF100-31-067,    1..........................  April 24, 2008.
 including Fokker Manual Change
 Notification-Operational Documentation
 MCNO-F100-50, dated January 31, 2008.
Fokker Service Bulletin SBF100-78-016...  Original...................  October 1, 1999.
Fokker Service Bulletin SBF100-78-017...  Original...................  December 1, 1999.
----------------------------------------------------------------------------------------------------------------

     (2) The Director of the Federal Register previously approved 
the incorporation by reference of Fokker Service Bulletin SBF100-31-
047, Revision 1, dated March 21, 1997; and Fokker Service Bulletin 
SBF100-31-051, dated August 15, 1998; on October 27, 1999 (64 FR 
51202, September 22, 1999).
    (3) For Fokker service information identified in this 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.
    (4) For AlliedSignal Grimes Aerospace and Honeywell service 
information identified in this 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.
    (5) You may review copies of the 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.
    (6) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on August 18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-20840 Filed 9-8-09; 8:45 am]

BILLING CODE 4910-13-P
