81 FR 40823 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 121 (June 23, 2016)

Page Range		40823-40825
FR Document		2016-14754
We propose to adopt a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This proposed AD was prompted by heavy corrosion found on the wing rear spar lower girder. This proposed AD would require inspections of the affected areas, modification of the wing trailing edge lower skin panels, and corrective actions if necessary. We are proposing this AD to detect and correct corrosion of the wing rear spar lower girder. This condition could reduce the load-carrying capability of the wing, possibly resulting in structural failure and loss of the airplane.
Federal Register, Volume 81 Issue 121 (Thursday, June 23, 2016)
[Federal Register Volume 81, Number 121 (Thursday, June 23, 2016)]
[Proposed Rules]
[Pages 40823-40825]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-14754]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 121 / Thursday, June 23, 2016 / 
Proposed Rules

[[Page 40823]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7271; Directorate Identifier 2015-NM-099-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 all 
Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This 
proposed AD was prompted by heavy corrosion found on the wing rear spar 
lower girder. This proposed AD would require inspections of the 
affected areas, modification of the wing trailing edge lower skin 
panels, and corrective actions if necessary. We are proposing this AD 
to detect and correct corrosion of the wing rear spar lower girder. 
This condition could reduce the load-carrying capability of the wing, 
possibly resulting in structural failure and loss of the airplane.

DATES: We must receive comments on this proposed AD by August 8, 2016.

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 [email protected]; 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-
7271; 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-2016-7271; 
Directorate Identifier 2015-NM-099-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0113, dated June 22, 2015 (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 F.28 Mark 0070, and 0100 airplanes. The MCAI states:

    On an F28 Mark 0070 aeroplane, heavy corrosion was found on the 
wing rear spar lower girder. At small spots the effective thickness 
of the vertical flange of the lower girder was almost lost. 
Subsequently, a number of inspections were accomplished on other 
aeroplanes to provide additional information on possible corrosion 
in this area. Because the rear spar lower girder between Wing 
Stations (WSTA) 9270 and 11794 is hidden from view by the inboard 
and outboard aileron balancing plates, it is possible that corrosion 
in this area remains undetected during the zonal inspections in zone 
536 and 636 (MRB tasks 062505-00-01 and 062605-00-01).The heavy 
corrosion was not only found in the area between WSTA 9270 and 
11794, but also in the area where the rear spar lower girder is 
directly visible.
    This condition, if not detected and corrected, reduces the load 
carrying capability of the wing, possibly resulting in structural 
failure and loss of the aeroplane.
    To address this potential unsafe condition, Fokker Services 
issued Service Bulletin (SB) SBF100-57-049 to provide instructions 
to detect and remove corrosion and to modify the wing trailing edge 
lower skin panels into access panels. SBF100-57-050 was issued to 
provide repair instructions.
    For the reasons described above, this [EASA] AD requires 
inspections of the affected areas and, depending on findings, 
accomplishment of applicable corrective action(s). This [EASA] AD 
also requires modification of the wing trailing edge lower skin 
panels into access panels [This modification is to provide ease of 
access for later inspection and repairs in the affected areas.], and 
reporting of the results of the inspections to Fokker Services.
    More information on this subject can be found in Fokker Services 
All Operators Message AOF100.197.

    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-
7271.

[[Page 40824]]

Related Service Information Under 1 CFR Part 51

    We reviewed Fokker Service Bulletin SBF100-57-049, dated March 24, 
2015, which describes procedures for an inspection for corrosion of 
certain wing rear spar lower girder areas, modification of the wing 
trailing edge lower skin panels, and corrective actions if necessary. 
We also reviewed Fokker Service Bulletin SBF100-57-050, Revision 1, 
dated May 19, 2015, which describes procedures for repair of the wing 
spar. 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.

Costs of Compliance

    We estimate that this proposed AD affects 8 airplanes of U.S. 
registry.
    We also estimate that it would take about 35 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $1,680 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $37,240, or $4,655 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 372 work-hours and require parts costing $7,600, for a cost 
of $39,220 per product. We have no way of determining the number of 
aircraft that might need this action.
    We also estimate that it would take about 1 work-hour per product 
for reporting. The average labor rate is $85 per work-hour. Based on 
these figures, we estimate the cost of this reporting on U.S. operators 
to be $680, or $85 per product.

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.

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-2016-7271; Directorate 
Identifier 2015-NM-099-AD.

(a) Comments Due Date

    We must receive comments by August 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Fokker Services B.V. Model F.28 Mark 0070 
and 0100 airplanes, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by heavy corrosion found on the wing rear 
spar lower girder. We are issuing this AD to detect and correct 
corrosion of the wing rear spar lower girder. This condition could 
reduce the load-carrying capability of the wing, possibly resulting 
in structural failure and loss of the airplane.

(f) Compliance

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

(g) Inspection of the Wing Rear Spar Lower Girder From Wing Station 
(WSTA) 9270 to 11794

    Within 1,000 flight cycles or 12 months, whichever occurs first 
after the effective date of this AD, accomplish a one-time detailed 
visual inspection for corrosion of the wing rear spar lower girder 
area from WSTA 9270 to 11794, in accordance with Part 1 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-57-
049, dated March 24, 2015.

[[Page 40825]]

(h) Modification of Wing Trailing Edge

    Within 1,000 flight cycles or 12 months, whichever occurs first 
after the effective date of this AD, modify the wing trailing edge 
lower skin panels into access panels, in accordance with Part 1 of 
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
57-049, dated March 24, 2015.

(i) Inspection of the Wing Rear Spar Lower Girder From WSTA 2635 to 
8700 and WSTA 11794 to 12975

    Within 2,000 flight cycles or 24 months, whichever occurs first 
after the effective date of this AD, accomplish a one-time detailed 
visual inspection for corrosion of the wing rear spar lower girder 
area from WSTA 2635 to 8700 and WSTA 11794 to 12975, in accordance 
with Part 2 of the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-57-049, dated March 24, 2015.

(j) Modification of Wing Rear Spar Lower Girder

    (1) If during any inspection required by paragraph (g) or (i) of 
this AD, as applicable, corrosion is found, before further flight, 
remove the corrosion and determine the remaining thickness at the 
damaged spots, in accordance with the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-57-049, dated March 24, 2015. If the 
remaining thickness at the damaged spots, as determined by this 
paragraph, is not within the tolerances specified in Fokker Service 
Bulletin SBF100-57-049, dated March 24, 2015, except as required by 
paragraph (k)(1) of this AD: Before further flight, accomplish the 
applicable corrective actions as defined in paragraph (j)(1)(i) or 
(j)(1)(ii) of this AD, as applicable.
    (i) For corrosion damage found outboard of WSTA 8200 only: 
Repair in accordance with the Accomplishment Instructions of Fokker 
Service Bulletin SBF100-57-050, Revision 1, dated May 19, 2015.
    (ii) Repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Fokker Services 
B.V.'s EASA Design Organization Approval (DOA).
    (2) If during any inspection required by paragraph (g) or (i) of 
this AD, only damage to the surface protection is found, or if the 
remaining thickness at the damaged spots, as determined by paragraph 
(j)(1) of this AD, is within the tolerances specified in Fokker 
Service Bulletin SBF100-57-049, dated March 24, 2015, except as 
required by paragraph (k)(1) of this AD: Before further flight, 
restore the surface protection in accordance with the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-57-049, dated March 
24, 2015, except as required by paragraph (k)(2) of this AD.

(k) Exceptions to Service Information Specifications

    (1) Where Fokker Service Bulletin SBF100-57-049, dated March 24, 
2015, specifies the acceptability of smaller thickness or customized 
repairs: Before further flight, obtain acceptable tolerances, using 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Fokker Services 
B.V.'s EASA DOA.
    (2) Where Fokker Service Bulletin SBF100-57-049, dated March 24, 
2015, specifies contacting Fokker for a customized repair: Before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Fokker Services B.V.'s EASA DOA.

(l) Reporting Requirements

    Submit a report of the findings both positive and negative of 
the inspection required by paragraph (g) and (i) of this AD to 
Fokker Services, in accordance with the Accomplishment Instructions 
of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, at 
the time specified in paragraph (l)(1) or (l)(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.

(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, WA 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) 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 the EASA; 
or Fokker Service B.V.'s EASA DOA. If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (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 
(MCAI) EASA Airworthiness Directive 2015-0113, dated June 22, 2015, 
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-2016-7271.
    (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 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 June 14, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-14754 Filed 6-22-16; 8:45 am]
 BILLING CODE 4910-13-P
40823

Proposed Rules Federal Register
Vol. 81, No. 121

Thursday, June 23, 2016

This section of the FEDERAL REGISTER For service information identified in substantive verbal contact we receive
contains notices to the public of the proposed this NPRM, contact Fokker Services about this proposed AD.
issuance of rules and regulations. The B.V., Technical Services Dept., P.O. Box
purpose of these notices is to give interested Discussion
1357, 2130 EL Hoofddorp, the
persons an opportunity to participate in the Netherlands; telephone +31 (0)88–6280–
rule making prior to the adoption of the final The European Aviation Safety Agency
rules.
350; fax +31 (0)88–6280–111; email (EASA), which is the Technical Agent
technicalservices@fokker.com; Internet for the Member States of the European
http://www.myfokkerfleet.com. You may Union, has issued EASA Airworthiness
DEPARTMENT OF TRANSPORTATION view this referenced service information Directive 2015–0113, dated June 22,
at the FAA, Transport Airplane 2015 (referred to after this as the
Federal Aviation Administration Directorate, 1601 Lind Avenue SW., Mandatory Continuing Airworthiness
Renton, WA. For information on the Information, or ‘‘the MCAI’’), to correct
14 CFR Part 39 availability of this material at the FAA, an unsafe condition for all Fokker
call 425–227–1221. Services B.V. Model F.28 Mark 0070,
[Docket No. FAA–2016–7271; Directorate
Identifier 2015–NM–099–AD] Examining the AD Docket and 0100 airplanes. The MCAI states:
On an F28 Mark 0070 aeroplane, heavy
RIN 2120–AA64 You may examine the AD docket on
corrosion was found on the wing rear spar
the Internet at http:// lower girder. At small spots the effective
Airworthiness Directives; Fokker www.regulations.gov by searching for thickness of the vertical flange of the lower
Services B.V. Airplanes and locating Docket No. FAA–2016– girder was almost lost. Subsequently, a
7271; or in person at the Docket number of inspections were accomplished on
AGENCY: Federal Aviation Management Facility between 9 a.m. other aeroplanes to provide additional
Administration (FAA), DOT. and 5 p.m., Monday through Friday, information on possible corrosion in this
ACTION: Notice of proposed rulemaking except Federal holidays. The AD docket area. Because the rear spar lower girder
(NPRM). contains this proposed AD, the between Wing Stations (WSTA) 9270 and
regulatory evaluation, any comments 11794 is hidden from view by the inboard
SUMMARY: We propose to adopt a new and outboard aileron balancing plates, it is
received, and other information. The
airworthiness directive (AD) for all possible that corrosion in this area remains
street address for the Docket Operations
Fokker Services B.V. Model F.28 Mark undetected during the zonal inspections in
office (telephone 800–647–5527) is in
0070 and 0100 airplanes. This proposed zone 536 and 636 (MRB tasks 062505–00–01
the ADDRESSES section. Comments will
AD was prompted by heavy corrosion and 062605–00–01).The heavy corrosion was
be available in the AD docket shortly not only found in the area between WSTA
found on the wing rear spar lower
after receipt. 9270 and 11794, but also in the area where
girder. This proposed AD would require
inspections of the affected areas, FOR FURTHER INFORMATION CONTACT: Tom the rear spar lower girder is directly visible.
modification of the wing trailing edge Rodriguez, Aerospace Engineer, This condition, if not detected and
International Branch, ANM 116, corrected, reduces the load carrying
lower skin panels, and corrective capability of the wing, possibly resulting in
actions if necessary. We are proposing Transport Airplane Directorate, FAA,
structural failure and loss of the aeroplane.
this AD to detect and correct corrosion 1601 Lind Avenue SW., Renton, WA
To address this potential unsafe condition,
of the wing rear spar lower girder. This 98057–3356; telephone 425–227–1137; Fokker Services issued Service Bulletin (SB)
condition could reduce the load- fax 425–227–1149. SBF100–57–049 to provide instructions to
carrying capability of the wing, possibly SUPPLEMENTARY INFORMATION: detect and remove corrosion and to modify
resulting in structural failure and loss of the wing trailing edge lower skin panels into
the airplane. Comments Invited access panels. SBF100–57–050 was issued to
DATES: We must receive comments on
provide repair instructions.
We invite you to send any written
For the reasons described above, this
this proposed AD by August 8, 2016. relevant data, views, or arguments about [EASA] AD requires inspections of the
ADDRESSES: You may send comments, this proposed AD. Send your comments affected areas and, depending on findings,
using the procedures found in 14 CFR to an address listed under the accomplishment of applicable corrective
11.43 and 11.45, by any of the following ADDRESSES section. Include ‘‘Docket No. action(s). This [EASA] AD also requires
methods: FAA–2016–7271; Directorate Identifier modification of the wing trailing edge lower
• Federal eRulemaking Portal: Go to 2015–NM–099–AD’’ at the beginning of skin panels into access panels [This
http://www.regulations.gov. Follow the your comments. We specifically invite modification is to provide ease of access for
instructions for submitting comments. comments on the overall regulatory, later inspection and repairs in the affected
• Fax: 202–493–2251. economic, environmental, and energy areas.], and reporting of the results of the
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS

inspections to Fokker Services.
• Mail: U.S. Department of aspects of this proposed AD. We will
More information on this subject can be
Transportation, Docket Operations, M– consider all comments received by the
found in Fokker Services All Operators
30, West Building Ground Floor, Room closing date and may amend this Message AOF100.197.
W12–140, 1200 New Jersey Avenue SE., proposed AD based on those comments.
Washington, DC 20590. We will post all comments we You may examine the MCAI in the
• Hand Delivery: Deliver to Mail receive, without change, to http:// AD docket on the Internet at http://
address above between 9 a.m. and 5 www.regulations.gov, including any www.regulations.gov by searching for
p.m., Monday through Friday, except personal information you provide. We and locating Docket No. FAA–2016–
Federal holidays. will also post a report summarizing each 7271.

VerDate Sep<11>2014 17:14 Jun 22, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\23JNP1.SGM 23JNP1
40824 Federal Register / Vol. 81, No. 121 / Thursday, June 23, 2016 / Proposed Rules

Related Service Information Under 1 to penalty for failure to comply with a 4. Will not have a significant
CFR Part 51 collection of information subject to the economic impact, positive or negative,
We reviewed Fokker Service Bulletin requirements of the Paperwork on a substantial number of small entities
SBF100–57–049, dated March 24, 2015, Reduction Act unless that collection of under the criteria of the Regulatory
which describes procedures for an information displays a current valid Flexibility Act.
inspection for corrosion of certain wing OMB control number. The control List of Subjects in 14 CFR Part 39
rear spar lower girder areas, number for the collection of information
required by this proposed AD is 2120– Air transportation, Aircraft, Aviation
modification of the wing trailing edge
0056. The paperwork cost associated safety, Incorporation by reference,
lower skin panels, and corrective
with this proposed AD has been Safety.
actions if necessary. We also reviewed
Fokker Service Bulletin SBF100–57– detailed in the Costs of Compliance The Proposed Amendment
050, Revision 1, dated May 19, 2015, section of this document and includes
Accordingly, under the authority
which describes procedures for repair of time for reviewing instructions, as well
delegated to me by the Administrator,
the wing spar. This service information as completing and reviewing the
the FAA proposes to amend 14 CFR part
is reasonably available because the collection of information. Therefore, all
39 as follows:
interested parties have access to it reporting associated with this proposed
through their normal course of business AD is mandatory. Comments concerning PART 39—AIRWORTHINESS
or by the means identified in the the accuracy of this burden and DIRECTIVES
ADDRESSES section. suggestions for reducing the burden
should be directed to the FAA at 800 ■ 1. The authority citation for part 39
FAA’s Determination and Requirements Independence Ave. SW., Washington, continues to read as follows:
of This Proposed AD DC 20591, ATTN: Information Authority: 49 U.S.C. 106(g), 40113, 44701.
This product has been approved by Collection Clearance Officer, AES–200.
the aviation authority of another § 39.13 [Amended]
country, and is approved for operation Authority for This Rulemaking
■ 2. The FAA amends § 39.13 by adding
in the United States. Pursuant to our Title 49 of the United States Code the following new airworthiness
bilateral agreement with the State of specifies the FAA’s authority to issue directive (AD):
Design Authority, we have been notified rules on aviation safety. Subtitle I, Fokker Services B.V.: Docket No. FAA–
of the unsafe condition described in the section 106, describes the authority of 2016–7271; Directorate Identifier 2015–
MCAI and service information the FAA Administrator. ‘‘Subtitle VII: NM–099–AD.
referenced above. We are proposing this Aviation Programs,’’ describes in more
(a) Comments Due Date
AD because we evaluated all pertinent detail the scope of the Agency’s
information and determined an unsafe authority. We must receive comments by August 8,
condition exists and is likely to exist or We are issuing this rulemaking under 2016.
develop on other products of the same the authority described in ‘‘Subtitle VII, (b) Affected ADs
type design. Part A, Subpart III, Section 44701: None.
General requirements.’’ Under that
Costs of Compliance section, Congress charges the FAA with (c) Applicability
We estimate that this proposed AD promoting safe flight of civil aircraft in This AD applies to all Fokker Services B.V.
affects 8 airplanes of U.S. registry. air commerce by prescribing regulations Model F.28 Mark 0070 and 0100 airplanes,
We also estimate that it would take for practices, methods, and procedures certificated in any category.
about 35 work-hours per product to the Administrator finds necessary for (d) Subject
comply with the basic requirements of safety in air commerce. This regulation Air Transport Association (ATA) of
this proposed AD. The average labor is within the scope of that authority America Code 57, Wings.
rate is $85 per work-hour. Required because it addresses an unsafe condition (e) Reason
parts would cost about $1,680 per that is likely to exist or develop on
product. Based on these figures, we products identified in this rulemaking This AD was prompted by heavy corrosion
estimate the cost of this proposed AD on found on the wing rear spar lower girder. We
action. are issuing this AD to detect and correct
U.S. operators to be $37,240, or $4,655 corrosion of the wing rear spar lower girder.
per product. Regulatory Findings
This condition could reduce the load-
In addition, we estimate that any We determined that this proposed AD carrying capability of the wing, possibly
necessary follow-on actions would take would not have federalism implications resulting in structural failure and loss of the
about 372 work-hours and require parts under Executive Order 13132. This airplane.
costing $7,600, for a cost of $39,220 per proposed AD would not have a (f) Compliance
product. We have no way of substantial direct effect on the States, on
Comply with this AD within the
determining the number of aircraft that the relationship between the national compliance times specified, unless already
might need this action. Government and the States, or on the done.
We also estimate that it would take distribution of power and
about 1 work-hour per product for responsibilities among the various (g) Inspection of the Wing Rear Spar Lower
reporting. The average labor rate is $85 Girder From Wing Station (WSTA) 9270 to
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levels of government.
11794
per work-hour. Based on these figures, For the reasons discussed above, I
we estimate the cost of this reporting on certify this proposed regulation: Within 1,000 flight cycles or 12 months,
U.S. operators to be $680, or $85 per 1. Is not a ‘‘significant regulatory whichever occurs first after the effective date
of this AD, accomplish a one-time detailed
product. action’’ under Executive Order 12866;
visual inspection for corrosion of the wing
2. Is not a ‘‘significant rule’’ under the rear spar lower girder area from WSTA 9270
Paperwork Reduction Act DOT Regulatory Policies and Procedures to 11794, in accordance with Part 1 of the
A federal agency may not conduct or (44 FR 11034, February 26, 1979); Accomplishment Instructions of Fokker
sponsor, and a person is not required to 3. Will not affect intrastate aviation in Service Bulletin SBF100–57–049, dated
respond to, nor shall a person be subject Alaska; and March 24, 2015.

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Federal Register / Vol. 81, No. 121 / Thursday, June 23, 2016 / Proposed Rules 40825

(h) Modification of Wing Trailing Edge obtain acceptable tolerances, using a method collection is 2120–0056. Public reporting for
Within 1,000 flight cycles or 12 months, approved by the Manager, International this collection of information is estimated to
whichever occurs first after the effective date Branch, ANM–116, Transport Airplane be approximately 5 minutes per response,
of this AD, modify the wing trailing edge Directorate, FAA; or EASA; or Fokker including the time for reviewing instructions,
lower skin panels into access panels, in Services B.V.’s EASA DOA. completing and reviewing the collection of
accordance with Part 1 of the (2) Where Fokker Service Bulletin SBF100– information. All responses to this collection
Accomplishment Instructions of Fokker 57–049, dated March 24, 2015, specifies of information are mandatory. Comments
Service Bulletin SBF100–57–049, dated contacting Fokker for a customized repair: concerning the accuracy of this burden and
March 24, 2015. Before further flight, repair using a method suggestions for reducing the burden should
approved by the Manager, International be directed to the FAA at: 800 Independence
(i) Inspection of the Wing Rear Spar Lower Branch, ANM–116, Transport Airplane Ave. SW., Washington, DC 20591, Attn:
Girder From WSTA 2635 to 8700 and WSTA Directorate, FAA; or EASA; or Fokker Information Collection Clearance Officer,
11794 to 12975 Services B.V.’s EASA DOA. AES–200.
Within 2,000 flight cycles or 24 months, (l) Reporting Requirements (n) Related Information
whichever occurs first after the effective date
of this AD, accomplish a one-time detailed Submit a report of the findings both (1) Refer to Mandatory Continuing
visual inspection for corrosion of the wing positive and negative of the inspection Airworthiness Information (MCAI) EASA
rear spar lower girder area from WSTA 2635 required by paragraph (g) and (i) of this AD Airworthiness Directive 2015–0113, dated
to 8700 and WSTA 11794 to 12975, in to Fokker Services, in accordance with the June 22, 2015, for related information. This
accordance with Part 2 of the Accomplishment Instructions of Fokker MCAI may be found in the AD docket on the
Accomplishment Instructions of Fokker Service Bulletin SBF100–57–049, dated Internet at http://www.regulations.gov by
Service Bulletin SBF100–57–049, dated March 24, 2015, at the time specified in searching for and locating Docket No. FAA–
March 24, 2015. paragraph (l)(1) or (l)(2) of this AD. 2016–7271.
(1) If the inspection was done on or after (2) For service information identified in
(j) Modification of Wing Rear Spar Lower the effective date of this AD: Submit the this AD, contact Fokker Services B.V.,
Girder report within 30 days after the inspection. Technical Services Dept., P.O. Box 1357,
(1) If during any inspection required by (2) If the inspection was done before the 2130 EL Hoofddorp, the Netherlands;
paragraph (g) or (i) of this AD, as applicable, effective date of this AD: Submit the report telephone +31 (0)88–6280–350; fax +31
corrosion is found, before further flight, within 30 days after the effective date of this (0)88–6280–111; email technicalservices@
remove the corrosion and determine the AD. fokker.com; Internet http://
remaining thickness at the damaged spots, in www.myfokkerfleet.com. You may view this
accordance with the Accomplishment (m) Other FAA AD Provisions
service information at the FAA, Transport
Instructions of Fokker Service Bulletin The following provisions also apply to this Airplane Directorate, 1601 Lind Avenue SW.,
SBF100–57–049, dated March 24, 2015. If the AD: Renton, WA. For information on the
remaining thickness at the damaged spots, as (1) Alternative Methods of Compliance availability of this material at the FAA, call
determined by this paragraph, is not within (AMOCs): The Manager, International 425–227–1221.
the tolerances specified in Fokker Service Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested Issued in Renton, Washington, on June 14,
Bulletin SBF100–57–049, dated March 24,
using the procedures found in 14 CFR 39.19. 2016.
2015, except as required by paragraph (k)(1)
of this AD: Before further flight, accomplish In accordance with 14 CFR 39.19, send your Dionne Palermo,
the applicable corrective actions as defined request to your principal inspector or local Acting Manager, Transport Airplane
in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, Flight Standards District Office, as Directorate, Aircraft Certification Service.
as applicable. appropriate. If sending information directly [FR Doc. 2016–14754 Filed 6–22–16; 8:45 am]
(i) For corrosion damage found outboard of to the International Branch, send it to ATTN:
BILLING CODE 4910–13–P
WSTA 8200 only: Repair in accordance with Tom Rodriguez, Aerospace Engineer,
the Accomplishment Instructions of Fokker International Branch, ANM–116, Transport
Service Bulletin SBF100–57–050, Revision 1, Airplane Directorate, FAA, 1601 Lind
dated May 19, 2015. Avenue SW., Renton, WA 98057–3356; ENVIRONMENTAL PROTECTION
(ii) Repair using a method approved by the telephone 425–227–1137; fax 425–227–1149. AGENCY
Manager, International Branch, ANM–116, Information may be emailed to: 9-ANM-116-
Transport Airplane Directorate, FAA; or the AMOC-REQUESTS@faa.gov. Before using 40 CFR Part 52
European Aviation Safety Agency (EASA); or any approved AMOC, notify your appropriate
principal inspector, or lacking a principal [EPA–R07–OAR–2014–0213; FRL–9948–16–
Fokker Services B.V.’s EASA Design
inspector, the manager of the local flight Region 7]
Organization Approval (DOA).
(2) If during any inspection required by standards district office/certificate holding
district office. The AMOC approval letter Approval and Promulgation of
paragraph (g) or (i) of this AD, only damage
to the surface protection is found, or if the must specifically reference this AD. Implementation Plans; State of Iowa;
remaining thickness at the damaged spots, as (2) Contacting the Manufacturer: For any Infrastructure SIP Requirements for
determined by paragraph (j)(1) of this AD, is requirement in this AD to obtain corrective the 1997 and 2006 Fine Particulate
within the tolerances specified in Fokker actions from a manufacturer, the action must Matter (PM2.5) National Ambient Air
Service Bulletin SBF100–57–049, dated be accomplished using a method approved Quality Standards (NAAQS), and the
March 24, 2015, except as required by by the Manager, International Branch, ANM– Adoption of the 1997 PM2.5 Standard
paragraph (k)(1) of this AD: Before further 116, Transport Airplane Directorate, FAA; or
flight, restore the surface protection in the EASA; or Fokker Service B.V.’s EASA AGENCY: Environmental Protection
accordance with the Accomplishment DOA. If approved by the DOA, the approval Agency (EPA).
Instructions of Fokker Service Bulletin must include the DOA-authorized signature.
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ACTION: Proposed rule.
SBF100–57–049, dated March 24, 2015, (3) Reporting Requirements: A federal
except as required by paragraph (k)(2) of this agency may not conduct or sponsor, and a SUMMARY: The Environmental Protection
AD. person is not required to respond to, nor Agency (EPA) is proposing to approve
shall a person be subject to a penalty for
(k) Exceptions to Service Information elements of two State Implementation
failure to comply with a collection of
Specifications information subject to the requirements of Plan (SIP) submissions from the State of
(1) Where Fokker Service Bulletin SBF100– the Paperwork Reduction Act unless that Iowa for the Infrastructure SIP
57–049, dated March 24, 2015, specifies the collection of information displays a current Requirements for the 1997 and 2006
acceptability of smaller thickness or valid OMB Control Number. The OMB Fine Particulate Matter (PM2.5) National
customized repairs: Before further flight, Control Number for this information Ambient Air Quality Standards

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Document Created: 2018-02-08 07:41:35
Document Modified: 2018-02-08 07:41:35
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by August 8, 2016.
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.
FR Citation		81 FR 40823
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 40823 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 121 (June 23, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
