[Federal Register Volume 76, Number 25 (Monday, February 7, 2011)]
[Rules and Regulations]
[Pages 6541-6543]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-2162]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1114; Directorate Identifier 2010-NM-206-AD;
Amendment 39-16591; AD 2011-03-07]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Model F.28 Mark
0100, 1000, 2000, 3000, and 4000 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new 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:
Prompted by an accident * * *, the FAA published Special Federal
Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities
(JAA) published Interim Policy INT/POL/25/12. The design review
conducted by Fokker on the F28 in response to these regulations
revealed that, in case of a lightning strike, an ignition source can
develop in the wing tank vapour space during fuel transfer from bag
tank CWT [center wing tank], if the electrical power for refuelling
is not switched off after refuelling.
Service experience has revealed situations where the power
switch of the Fuelling Control Panel (FCP) appeared to be ``ON''
with the access panel closed. The cam on the access panel that
should operate the power switch, if forgotten by flight crew or
maintenance staff, can pivot away during closing of the panel, which
may result in the switch staying in the ``ON'' position.
This condition, if not corrected, could result in a wing fuel
tank explosion and consequent loss of the aeroplane.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective March 14, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 14,
2011.
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.
[[Page 6542]]
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 November 19, 2010
(75 FR 70861). That NPRM proposed to correct an unsafe condition for
the specified products. The MCAI states:
Prompted by an accident * * *, the FAA published Special Federal
Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities
(JAA) published Interim Policy INT/POL/25/12. The design review
conducted by Fokker on the F28 in response to these regulations
revealed that, in case of a lightning strike, an ignition source can
develop in the wing tank vapour space during fuel transfer from bag
tank CWT [center wing tank], if the electrical power for refuelling
is not switched off after refuelling.
Service experience has revealed situations where the power
switch of the Fuelling Control Panel (FCP) appeared to be ``ON''
with the access panel closed. The cam on the access panel that
should operate the power switch, if forgotten by flight crew or
maintenance staff, can pivot away during closing of the panel, which
may result in the switch staying in the ``ON'' position.
This condition, if not corrected, could result in a wing fuel
tank explosion and consequent loss of the aeroplane.
For the reasons described above, this [EASA] AD requires an
inspection of the cam and, depending on findings, replacement with
an improved part. Subsequently, this AD requires repetitive
functional checks of the cam and, depending on findings, the
necessary corrective actions.
The corrective action is adjusting the FCP cam until it operates
correctly. 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.
Costs of Compliance
We estimate that this AD will affect 6 products of U.S. registry.
We also estimate that it will take about 3 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $426 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 parts. 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 the U.S. operators
to be $4,086, or $681 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
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 adding the following new AD:
2011-03-07 Fokker Services B.V.: Amendment 39-16591. Docket No. FAA-
2010-1114; Directorate Identifier 2010-NM-206-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
14, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Fokker Services B.V. Model F.28 Mark
1000, 2000, 3000, and 4000 airplanes, all serial numbers, equipped
with a center wing tank (CWT); and Model F.28
[[Page 6543]]
Mark 0100 airplanes, serial numbers 11244 through 11441;
certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Prompted by an accident * * *, the FAA published Special Federal
Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities
(JAA) published Interim Policy INT/POL/25/12. The design review
conducted by Fokker on the F28 in response to these regulations
revealed that, in case of a lightning strike, an ignition source can
develop in the wing tank vapour space during fuel transfer from bag
tank CWT [center wing tank], if the electrical power for refuelling
is not switched off after refuelling.
Service experience has revealed situations where the power
switch of the Fuelling Control Panel (FCP) appeared to be ``ON''
with the access panel closed. The cam on the access panel that
should operate the power switch, if forgotten by flight crew or
maintenance staff, can pivot away during closing of the panel, which
may result in the switch staying in the ``ON'' position.
This condition, if not corrected, could result in a wing fuel
tank explosion and consequent loss of the aeroplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Initial Inspection and Corrective Actions
(g) Within 6 months after the effective date of this AD, inspect
the FCP cam to determine the part number (P/N), in accordance with
Part 1 of the Accomplishment Instructions of Fokker Service Bulletin
SBF28-28-052, dated April 20, 2010 (for Model F.28 Mark 1000, 2000,
3000, and 4000 airplanes); or SBF100-28-063, dated April 15, 2010
(for Model F.28 Mark 0100 airplanes).
(1) If the correct part number is installed (P/N D48127-009 for
Model F.28 Mark 0100 airplanes and P/N A42509-089 for Model F.28
Mark 1000, 2000, 3000, and 4000 airplanes), before further flight,
do an inspection to verify that the cam operates correctly, in
accordance with Part 1 of the Accomplishment Instructions of Fokker
Service Bulletin SBF28-28-052, dated April 20, 2010 (for Model F.28
Mark 1000, 2000, 3000, and 4000 airplanes); or SBF100-28-063, dated
April 15, 2010 (for Model F.28 Mark 0100 airplanes).
(2) If a part number other than P/N D48127-009 for Model F.28
Mark 0100 airplanes and P/N A42509-089 for Model F.28 Mark 1000,
2000, 3000, and 4000 airplanes is installed, within 24 months after
the effective date of this AD, replace the cam with a cam having a
correct part number, and do an inspection to verify that the cam
operates correctly, in accordance with Part 2 of the Accomplishment
Instructions of Fokker Service Bulletin SBF28-28-052, dated April
20, 2010 (for Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes);
or SBF100-28-063, dated April 15, 2010 (for Model F.28 Mark 0100
airplanes).
(3) If, during any inspection required by paragraphs (g)(1) and
(g)(2) of this AD, the cam does not operate correctly, before
further flight, adjust the cam until it operates correctly, in
accordance with Part 2 of the Accomplishment Instructions of Fokker
Service Bulletin SBF28-28-052, dated April 20, 2010 (for Model F.28
Mark 1000, 2000, 3000, and 4000 airplanes); or SBF100-28-063, dated
April 15, 2010 (for Model F.28 Mark 0100 airplanes).
Repetitive Inspections
(h) Within 1,200 flight hours after verifying that the cam
operates correctly, as required by paragraphs (g)(1) and (g)(2) of
this AD, as applicable: Do an inspection to verify that the cam
operates correctly and, before further flight, do all applicable
corrective actions, in accordance with Part 2 of the Accomplishment
Instructions of Fokker Service Bulletin SBF28-28-052, dated April
20, 2010 (for Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes);
or SBF100-28-063, dated April 15, 2010 (for Model F.28 Mark 0100
airplanes). Thereafter, repeat the inspection of the cam at
intervals not to exceed 1,200 flight hours.
Parts Installation
(i) As of the effective date of this AD, no person may install
an FCP access door, cam, or fueling panel on any airplane, unless
the requirements of this AD have been accomplished on the cam.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service
information as follows: Although paragraph (6) of the MCAI provides
an option to incorporate the repetitive functional inspection into
the maintenance program and then use the maintenance program as a
method of complying with the repetitive inspection requirement, this
AD does not include that provision.
Other FAA AD Provisions
(j) 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, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office. The AMOC approval letter must specifically reference this
AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
Related Information
(k) Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2010-0139, dated July 1, 2010; Fokker
Service Bulletin SBF28-28-052, dated April 20, 2010; and Fokker
Service Bulletin SBF100-28-063, dated April 15, 2010; for related
information.
Material Incorporated by Reference
(l) You must use Fokker Service Bulletin SBF28-28-052, dated
April 20, 2010; or Fokker Service Bulletin SBF100-28-063, dated
April 15, 2010; as applicable; to do the actions required by this
AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For 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
[email protected]; Internet http://www.myfokkerfleet.com.
(3) 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.
(4) 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 January 25, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-2162 Filed 2-4-11; 8:45 am]
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