
[Federal Register Volume 81, Number 222 (Thursday, November 17, 2016)]
[Proposed Rules]
[Pages 81018-81021]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-27529]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9389; Directorate Identifier 2014-NM-153-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 all 
Fokker Services B.V. Model F28 Mark 0100 series airplanes. This 
proposed AD was prompted by an evaluation by the design approval holder 
(DAH) indicating that certain wing fuel tank access panels are subject 
to widespread fatigue damage (WFD). This proposed AD would require 
replacement of affected access panels and modification of the coamings 
of the associated access holes. We are proposing this AD to prevent the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 3, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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: technicalservices@fokker.com; Internet: http://www.myfokkerfleet.com. You may view this 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 by searching for and locating Docket No. FAA-2016-
9389; or in person at the Docket Management Facility 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, WA 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-2016-9389; 
Directorate Identifier 2014-NM-153-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

    Fatigue damage can occur locally, in small areas or structural 
design details,

[[Page 81019]]

or globally, in widespread areas. Multiple-site damage is widespread 
damage that occurs in a large structural element such as a single rivet 
line of a lap splice joining two large skin panels. Widespread 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. This 
condition is known as widespread fatigue damage. It is associated with 
general degradation of large areas of structure with similar structural 
details and stress levels. 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 structural 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 DAHs 
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 action is necessary to enable DAHs 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 Union, has issued EASA AD 
2016-0125, dated June 21, 2016, which supersedes EASA AD 2014-0158, 
dated July 7, 2014 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Fokker Services B.V. Model F28 Mark 0100 series 
airplanes. The MCAI states:

    Based on findings on test articles, fatigue-induced cracks may 
develop in the coamings of certain wing fuel tank access panels Part 
Number (P/N) D12395-403 and P/N D12450-403, installed on Fokker F28 
Mark 0100 aeroplanes.
    To ensure the continued structural integrity with respect to 
fatigue, repetitive inspections were included in the Airworthiness 
Limitations Section (ALS) of the Instructions for Continued 
Airworthiness. Fokker Services also developed precautionary measures 
to reduce stress loads in the affected areas by replacement of the 
affected access panels with new panels, P/N D19701-401 and P/N 
D19701-403, having thinner skin, and a modification by introducing 
internal patches to the coamings of the affected access holes.
    These precautionary measures were introduced with Service 
Bulletins (SB) SBF100-57-027 and SBF100-57-028. As part of the 
Widespread Fatigue Damage re-evaluation, it was concluded that 
repetitive inspections through the ALS do not provide a sufficient 
level of protection against the fatigue-induced cracks.
    This condition, if not corrected, would affect the structural 
integrity of the lower wing skins of both outer wings in the areas 
surrounding the affected fuel tank access panels.
    For the reasons described above, this [EASA] AD requires 
replacement of the affected access panels and modification of the 
coamings of these access holes.
    Post-modification inspection requirements depend on the actual 
number of flight cycles accumulated at the moment of modification. 
Related detailed information is provided in SBF100-57-027 and 
SBF100-57-028, as well as in Fokker Services ALS Report SE-623 Issue 
12.
    Fokker Services All Operators Message AOF100.178#05 provides 
additional information concerning the subject addressed by this 
[EASA] AD.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9389.

Related Service Information Under 1 CFR Part 51

    Fokker Services B.V. has issued the following service information:
     Fokker Service Bulletin SBF 100-57-027, Revision 2, dated 
December 11, 2013. This service information provides instructions to 
replace certain fuel tank access panels.
     Fokker Service Bulletin SBF 100-57-028, Revision 2, dated 
December, 11, 2013. This service information provides instructions to 
modify the coamings of certain fuel tank access holes.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

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 Proposed AD and the MCAI or Service 
Information

    In the ``Required Action(s) and Compliance Times'' section of the 
MCAI, paragraphs (3) and (4) specify to incorporate or comply with 
certain maintenance tasks (repetitive inspections). These actions are 
not included in this proposed AD. Since EASA AD 2014-0158, dated July 
7, 2014, was issued, EASA issued AD 2016-0125, dated June 21, 2016, 
which includes a requirement to incorporate those maintenance tasks. We 
are considering further rulemaking to require the actions specified in 
EASA AD 2016-0125, dated June 21, 2016.

Costs of Compliance

    We estimate that this proposed AD affects 15 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 81020]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replacement and Modification..........  510 work-hours x $85 per         $45,500         $88,350      $1,325,250
                                         hour = $43,350 per
                                         airplane.
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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.

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 airworthiness 
directive (AD):

Fokker Services B.V.: Docket No. FAA-2016-9389; Directorate 
Identifier 2014-NM-153-AD.

(a) Comments Due Date

    We must receive comments by January 3, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Fokker Services B.V. Model F28 Mark 0100 
series airplanes, certificated in any category, all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that certain wing fuel tank access panels 
are subject to widespread fatigue damage (WFD). We are issuing this 
AD to prevent fatigue cracking in the wing structure, which could 
result in reduced structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Modification and Replacement

    Within 63,000 flight cycles since first flight of the airplane, 
or within 90 days after the effective date of this AD, whichever 
occurs later, accomplish the actions specified in paragraphs (g)(1) 
and (g)(2) of this AD, as applicable.
    (1) For airplanes identified in Fokker Service Bulletin SBF100-
57-028, Revision 2, dated December 11, 2013: Modify the coamings of 
the fuel tank access holes at the access panel locations identified 
in, and in accordance with the Accomplishment Instructions of Fokker 
Service Bulletin SBF100-57-028, Revision 2, dated December 11, 2013.
    (2) For airplanes identified in Fokker Service Bulletin SBF100-
57-027, Revision 2, dated December 11, 2013: Replace access panels 
having part number D12395-403 and D12450-403 with new panels having 
part number D19701-401 and D19701-403, at the access panel locations 
identified in, and in accordance with the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-57-027, Revision 2, 
dated December 11, 2013.

(h) Parts Installation Prohibition

    (1) For airplanes that, on the effective date of this AD, have 
an access panel with part number D12395-403 or D12450-403 installed 
at any of the affected locations: After accomplishing the actions 
required by paragraphs (g)(1) and (g)(2) of this AD, as applicable, 
no person may install, on any airplane, access panels having part 
number D12395-403 or D12450-403 at any access panel location as 
identified in Fokker Service Bulletin SBF100-57-027, Revision 2, 
dated December 11, 2013.
    (2) For airplanes that, on the effective date of this AD, do not 
have an access panel with part number D12395-403 or D12450-403 
installed at any of the affected locations: As of the effective date 
of this AD, no person may install, on any airplane, access panels 
having part number D12395-403 or D12450-403 at any access panel 
location as identified in Fokker Service Bulletin SBF100-57-027, 
Revision 2, dated December 11, 2013.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g)(1) of this AD, if those actions were performed before 
the effective date of this AD using the service information 
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD.
    (i) Fokker Service Bulletin SBF100-57-028, dated May 2, 1994.
    (ii) Fokker Service Bulletin SBF100-57-028, Revision 1, dated 
November 1, 1994.
    (2) This paragraph provides credit for actions required by 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using the service information 
specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
    (i) Fokker Service Bulletin SBF100-57-027, dated September 13, 
1993.
    (ii) Fokker Service Bulletin SBF100-57-027, Revision 1, dated 
May 2, 1994.

(j) Other FAA AD Provisions

    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.

[[Page 81021]]

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, WA 98057-3356; telephone: 425-227-1137; fax: 425-227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or European 
Aviation Safety Agency (EASA); or Fokker Services B.V.'s EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2014-0158, dated July 7, 2014, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2016-9389.
    (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: technicalservices@fokker.com; Internet: 
http://www.myfokkerfleet.com. You may view this 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 November 7, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-27529 Filed 11-16-16; 8:45 am]
 BILLING CODE 4910-13-P


