[Federal Register Volume 77, Number 24 (Monday, February 6, 2012)]
[Proposed Rules]
[Pages 5724-5726]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-2618]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0039; Directorate Identifier 2011-NM-144-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes.
This proposed AD was prompted by reports of cracks underneath the
passenger door in a butt-joint on the forward fuselage of an F.28 Mark
0100 airplane. This proposed AD would require repetitive low frequency
eddy current inspections of the forward fuselage butt-joints for
cracks, and if necessary, a temporary repair followed by a permanent
repair. We are proposing this AD to detect and correct cracks on the
butt-joint on the forward fuselage, which could result in explosive
decompression and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by March 22, 2012.
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 W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For 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; email [email protected];
Internet http://www.myfokkerfleet.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.
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-2012-0039;
Directorate Identifier 2011-NM-144-AD'' at the beginning of
[[Page 5725]]
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 2011-0115, dated June 17, 2011 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
A report has been received of a crack, detected in a butt-joint
on the forward fuselage of an F28 Mark 0100 aeroplane, underneath
the passenger door.
Investigations revealed that, depending on the configuration of
the aeroplane, one or two butt-joints in the forward fuselage can be
affected.
This condition, if not detected and corrected, could lead to
explosive decompression and consequent loss of the aeroplane.
For the reasons described above, this [EASA] AD requires
repetitive [low frequency eddy current] inspections of the forward
fuselage butt joints for cracks and, when a crack is detected,
accomplishment of a temporary repair. This [EASA] AD also requires
reporting any cracks found to Fokker Services to enable the
development of a modification and the determination of an interval
for a repetitive inspection task, to be incorporated in the ALI
[airworthiness limitations instructions] section of the MRB
[maintenance review board] document. This [EASA] AD is considered to
be an interim measure and further AD action is likely.
Required actions include a permanent repair of the forward fuselage
butt-joints. You may obtain further information by examining the MCAI
in the AD docket.
Relevant Service Information
Fokker Services B.V. has issued Service Bulletin SBF100-53-115,
dated June 16, 2011. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
Paragraph (2) of EASA AD 2011-0115, dated June 17, 2011, explains
that an optional alternative method for the inspection required by
paragraph (g) of this proposed AD may be used. This AD does not include
that optional alternative method, as the service information in this AD
does not provide enough detail regarding this method.
EASA AD 2011-0115, dated June 17, 2011, does not include a
permanent repair. This proposed AD does require a permanent repair.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 4 products of U.S. registry. We also estimate that
it would take about 3 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $1,020, or $255 per product.
In addition, we estimate that any necessary follow-on actions would
take about 40 work-hours and require parts costing $0, for a cost of
$3,400 per product. We have no way of determining the number of
products that may need these actions.
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 affect intrastate aviation in Alaska; and
4. 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Fokker Services B.V.: Docket No. FAA-2012-0039; Directorate
Identifier 2011-NM-144-AD.
(a) Comments Due Date
We must receive comments by March 22, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and
0100 airplanes, as identified in Fokker Service Bulletin SBF100-53-
115, dated June 16, 2011.
[[Page 5726]]
(d) Subject
Air Transport Association (ATA) of America Code 53: Fuselage.
(e) Reason
This AD was prompted by reports of cracks underneath the
passenger door in a butt-joint on the forward fuselage of an F.28
Mark 0100 airplane. We are issuing this AD to detect and correct
cracks on the butt-joint on the forward fuselage, which could result
in explosive decompression and consequent loss of control of the
airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Inspection
Before the accumulation of 20,000 total flight cycles, or within
180 flight cycles after the effective date of this AD, whichever
occurs later, do a low frequency eddy current inspection of the
forward fuselage butt-joints for cracks, in accordance with the
Accomplishment Instructions of Fokker Service Bulletin SBF100-53-
115, dated June 16, 2011. Repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles. Doing the temporary
repair in paragraph (h) of this AD is terminating action for the
repetitive inspections required by this paragraph. The temporary
repair can also be accomplished if no cracking is found.
(h) Temporary Repair
If any cracking is found during any inspection required by
paragraph (g) of this AD, before further flight, do a temporary
repair, in accordance with the Accomplishment Instructions of Fokker
Service Bulletin SBF100-53-115, dated June 16, 2011. Doing the
temporary repair is terminating action for the repetitive
inspections required by paragraph (g) of this AD.
(i) Permanent Repair
Within 10,000 flight cycles after installing the temporary
repair as required by paragraph (h) of this AD, install a permanent
repair using a method approved by the Manager, International Branch,
ANM 116, Transport Airplane Directorate, FAA.
(j) Reporting
Submit a report of the findings (both positive and negative), to
Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150
AE Nieuw-Vennep, the Netherlands, using the reports form of Fokker
Service Bulletin SBF100-53-115, dated June 16, 2011, of the
inspection required by paragraph (g) of this AD, at the applicable
time specified in paragraph (j)(1) or (j)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
(k) Other FAA AD Provisions
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. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the International Branch, send it
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. Information may be emailed to: [email protected]. 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.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(l) Related Information
Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2011-0115, dated June 17, 2011; and Fokker Service
Bulletin SBF100-53-115, dated June 16, 2011; for related
information.
Issued in Renton, Washington, on January 12, 2012.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-2618 Filed 2-3-12; 8:45 am]
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