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)

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, Number 121 (Thursday, June 23, 2016)]
[Proposed Rules]
[Pages 40823-40825]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-14754]


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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.

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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).

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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