[Federal Register Volume 78, Number 205 (Wednesday, October 23, 2013)]
[Proposed Rules]
[Pages 63132-63135]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-24795]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0865; Directorate Identifier 2012-NM-199-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
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 an evaluation by the design approval
holder (DAH) indicating that the butt-joints on the forward fuselage
above the passenger door are subject to widespread fatigue damage
(WFD). This proposed AD would require inspecting the forward fuselage
butt-joints for cracking, repairing any crack, and eventually doing a
terminating repair. We are proposing this AD to prevent fatigue
cracking of such butt-joints, which could result in reduced structural
integrity of the airplane and in-flight decompression of the airplane.
DATES: We must receive comments on this proposed AD by December 9,
2013.
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 1357, 2130 EL
Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31
(0)88-6280-111; 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, WA. 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 MCAI, 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-2013-0865;
Directorate Identifier 2012-NM-199-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
Structural fatigue damage is progressive. It begins as minute
cracks, and those cracks grow under the action of repeated stresses.
This can happen because of normal operational conditions and design
attributes, or because of isolated situations or incidents such as
material defects, poor fabrication quality, or corrosion pits, dings,
or scratches. Fatigue damage can occur locally, in small areas or
structural design details, or globally. Global fatigue damage is
general degradation of large areas of structure with similar structural
details and stress levels. Multiple-site damage is global damage that
occurs in a large structural
[[Page 63133]]
element such as a single rivet line of a lap splice joining two large
skin panels. Global damage can also occur in multiple elements such as
adjacent frames or stringers. Multiple-site-damage and multiple-
element-damage cracks are typically too small initially to be reliably
detected with normal inspection methods. Without intervention, these
cracks will grow, and eventually compromise the structural integrity of
the airplane, in a condition known as WFD. As an airplane ages, WFD
will likely occur, and will certainly occur if the airplane is operated
long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent catastrophic failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that design
approval holders establish a limit of validity (LOV) of the engineering
data that support the structural maintenance program. Operators
affected by the WFD rule may not fly an airplane beyond its LOV, unless
an extended LOV is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this approach is necessary to enable design
approval holders to propose LOVs that allow operators the longest
operational lives for their airplanes, and still ensure that WFD will
not occur. This approach allows for an implementation strategy that
provides flexibility to DAHs in determining the timing of service
information development (with FAA approval), while providing operators
with certainty regarding the LOV applicable to their airplanes.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0218, dated October 19, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``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, above the
passenger door. Investigation results revealed that, depending on
the configuration of the aeroplane, four butt joints in the forward
fuselage can be affected, at stringers 8, 37, 42 and 67 between
fuselage stations 3850 and 5305.
This condition, if not detected and corrected, can result in an
exponential crack growth rate, possibly leading to failure of the
butt-joint over a certain length and consequent in-flight
decompression of the aeroplane.
For the reasons described above, this [EASA] AD requires a one-
time inspection [low frequency eddy current] of the forward fuselage
butt joints for cracks and, depending on findings, accomplishment of
a temporary repair [including a detailed inspection for cracks in
the butt strap on the inside of the applicable joint, and corrective
actions if necessary] and reporting the findings to Fokker Services.
In addition, this AD requires a permanent repair/modification [and a
detailed inspection for cracks in the butt strap on the inside of
the applicable joint, and corrective actions if necessary].
* * * * *
Corrective actions include removing the cracked part of the butt
joint and installing an insert, and installing of an external repair
strap. You may obtain further information by examining the MCAI in the
AD docket.
Relevant Service Information
Fokker Services B.V. has issued Fokker Service Bulletin SBF100-53-
118, Revision 2, dated October 16, 2012; and Fokker Service Bulletin
SBF100-53-119, Revision 2, dated May 8, 2013. 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
The MCAI specifies an alternative detailed visual inspection of the
butt-joints from the inside of the fuselage. This proposed AD would not
allow that inspection, and the difference has been coordinated with
EASA.
Explanation of Compliance Time
The compliance time for the modification specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is modified before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. We will not grant any extensions of the
compliance time to complete any AD-mandated service bulletin related to
WFD without extensive new data that would substantiate and clearly
warrant such an extension.
Costs of Compliance
We estimate that this proposed AD affects 4 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection.................................. 127 work-hours $0 $10,795 $43,180
x $85 per hour
= $10,795
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need these
repairs:
[[Page 63134]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair.................................... 30 work-hours x $85 per hour = $0 $2,550
$2,550.
----------------------------------------------------------------------------------------------------------------
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to 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 control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is 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.
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);
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
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:
Fokker Services B.V.: Docket No. FAA-2013-0865; Directorate
Identifier 2012-NM-199-AD.
(a) Comments Due Date
We must receive comments by December 9, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and
0100 airplanes, certificated in any category, as identified in
Fokker Service Bulletin SBF100-53-118, Revision 2, dated October 16,
2012.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the butt-joints on the forward fuselage
above the passenger door are subject to widespread fatigue damage
(WFD). We are issuing this AD to prevent fatigue cracking of such
butt-joints, which could result in reduced structural integrity of
the airplane and in-flight decompression 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 35,000 total flight cycles, or within
8 months after the effective date of this AD, whichever occurs
later: Do a low frequency eddy current inspection for cracking of
the forward fuselage butt-joints, in accordance with the
Accomplishment Instructions of Fokker Service Bulletin SBF100-53-
118, Revision 2, dated October 16, 2012.
(h) Repair
If any cracking is found during the inspection specified in
paragraph (g) of this AD, before further flight, do the actions
specified in either paragraph (h)(1) or (h)(2) of this AD.
(1) Accomplish a temporary repair, including a detailed
inspection for cracks in the butt strap on the inside of the
applicable joint, and all applicable corrective actions, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF100-53-118, Revision 2, dated October 16, 2012.
(2) Do a terminating repair of the forward fuselage butt-joints,
including a detailed inspection for cracks in the butt strap on the
inside of the applicable joint, and all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Fokker Service Bulletin SBF100-53-119, Revision 2, dated May 8,
2013. Accomplishing the terminating repair specified in this
paragraph is a method of compliance with the terminating repair
required by paragraph (j) of this AD.
(i) Reporting
Submit a report of any crack findings from the inspection
specified in paragraph (g) of this AD to Fokker Services, Hoeksteen
40, 2132 MS Hoofddorp, PO Box 1357, 2130 EL Hoofddorp, The
Netherlands; by using the Reporting Form (figure 14 and figure 15,
as applicable) of Fokker Service Bulletin SBF100-53-118, Revision 2,
dated October 16, 2012; at the applicable time specified in
paragraph (i)(1) or (i)(2) of this AD.
[[Page 63135]]
(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.
(j) Terminating Repair
Before the accumulation 50,000 total flight cycles, or within 8
months after the effective date of this AD, whichever occurs later:
Do the terminating repair of the forward fuselage butt-joints,
including a detailed inspection for cracks in the butt strap on the
inside of the applicable joint, and all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Fokker Service Bulletin SBF100-53-119, Revision 2, dated May 8,
2013. Do all applicable corrective actions before further flight.
(k) Credit for Previous Actions
(1) This paragraph provides credit for applicable actions
required by paragraphs (g) and (h)(1) of this AD, if those actions
were performed before the effective date of this AD using the
service bulletins specified in paragraphs (k)(1)(i) or (k)(1)(ii) of
this AD, which are not incorporated by reference in this AD.
(i) Fokker Service Bulletin SBF100-53-118, dated April 10, 2012.
(ii) Fokker Service Bulletin SBF100-53-118, Revision 1, dated
July 6, 2012.
(2) This paragraph provides credit for actions required by
paragraphs (h)(2) and (j) of this AD, if those actions were
performed before the effective date of this AD using the service
bulletins specified in paragraphs (k)(2)(i) or (k)(2)(ii) of this
AD, which are not incorporated by reference in this AD.
(i) Fokker Service Bulletin SBF100-53-119, dated June 20, 2012.
(ii) Fokker Service Bulletin SBF100-53-119, Revision 1, dated
October 30, 2012.
(l) Compliance Time Provisions
No alternative compliance times may be used for the modification
required by paragraph (j) of this AD, unless extensive new data are
provided and the compliance time is approved as an alternative
method of compliance (AMOC) in accordance with the procedures
specified in paragraph (m) of this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
European Aviation Safety Agency Airworthiness Directive 2012-0218,
dated October 19, 2012, for related information, which can be found
in the AD docket on the Internet at http://www.regulations.gov.
(2) For service information identified in this AD, contact
Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130
EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31
(0)88-6280-111; 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, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on September 30, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-24795 Filed 10-22-13; 8:45 am]
BILLING CODE 4910-13-P