81 FR 87419 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 233 (December 5, 2016)

We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by heavy corrosion found on the wing rear spar lower girder. This AD requires inspections of the affected areas, modification of the wing trailing edge lower skin panels, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.

[Federal Register Volume 81, Number 233 (Monday, December 5, 2016)]
[Rules and Regulations]
[Pages 87419-87422]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-28601]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7271; Directorate Identifier 2015-NM-099-AD; 
Amendment 39-18722; AD 2016-24-05]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD 
was prompted by heavy corrosion found on the wing rear spar lower 
girder. This AD requires inspections of the affected areas, 
modification of the wing trailing edge lower skin panels, and 
corrective actions if necessary. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective January 9, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 9, 
2017.

ADDRESSES: For service information identified in this final rule, 
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. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-7271.

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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Fokker Services B.V. 
Model F28 Mark 0070 and 0100 airplanes. The NPRM published in the 
Federal Register on June 23, 2016 (81 FR 40823) (``the NPRM'').
    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 F28 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 [Maintenance Review Board] 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) [including 
removing corrosion, repair, and restoring protective finish]. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

[[Page 87420]]

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.

Costs of Compliance

    We estimate that this AD affects 8 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Wing inspection and              35 work-hours x $85 per          $1,680  $4,655 per          $37,240 per
 modification.                    hour = $2,975 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
Reporting......................  1 work hour x $85 per                 0  85................  680.
                                  hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary corrective 
actions that will be required based on the results of the required 
inspection. We have no way of determining the number of airplanes that 
might need these corrective actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                       Labor cost              Parts cost             Cost per product
----------------------------------------------------------------------------------------------------------------
Corrective Actions...............  Up to 372 work hours x     Up to $7,600........  Up to $39,220.
                                    $85 per hour = $31,620.
----------------------------------------------------------------------------------------------------------------

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 AD is 2120-
0056. The paperwork cost associated with this 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 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2016-24-05 Fokker Services B.V.: Amendment 39-18722; Docket No. FAA-
2016-7271; Directorate Identifier 2015-NM-099-AD.

(a) Effective Date

    This AD is effective January 9, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Fokker Services B.V. Model F28 Mark 0070 
and 0100 airplanes, certificated in any category.

(d) Subject

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

[[Page 87421]]

(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 Stations 
(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.

(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) Corrective Actions for the Inspections 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 inspections required by paragraphs (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, Transport Airplane Directorate, 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.
    (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

    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.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Fokker Service Bulletin SBF100-57-049, dated March 24, 2015.
    (ii) Fokker Service Bulletin SBF100-57-050, Revision 1, dated 
May 19, 2015.
    (3) 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.
    (4) 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.

[[Page 87422]]

    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 17, 2016.
Phil Forde,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-28601 Filed 12-2-16; 8:45 am]
BILLING CODE 4910-13-P