AD 2017-01-04

[Federal Register Volume 82, Number 11 (Wednesday, January 18, 2017)]
[Rules and Regulations]
[Pages 5365-5367]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-00410]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9058; Directorate Identifier 2016-NM-024-AD; 
Amendment 39-18771; AD 2017-01-04]
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 certain 
Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was 
prompted by an analysis which determined that, for certain areas of the 
fuselage, the current threshold of an Airworthiness Limitations Section 
inspection is insufficient to detect early crack development. This AD 
requires one time high and low frequency eddy current inspections of 
the affected fuselage skin for cracks, and repair if necessary. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective February 22, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 22, 
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: <a href="/cdn-cgi/l/email-protection#0e7a6b6d6660676d6f627d6b7c78676d6b7d4e686165656b7c206d6163"><span class="__cf_email__" data-cfemail="ec98898f8482858f8d809f899e9a858f899fac8a838787899ec28f8381">[email&#160;protected]</span></a>; Internet 
<a href="http://www.myfokkerfleet.com">http://www.myfokkerfleet.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2016-9058.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9058; 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 certain Fokker Services 
B.V. Model F28 Mark 0100 airplanes. The NPRM published in the Federal 
Register on September 8, 2016 (81 FR 62029) (``the NPRM''). The NPRM 
was prompted by an analysis which determined that, for certain areas of 
the fuselage, the current threshold of an Airworthiness Limitations 
Section inspection is insufficient to detect early crack development. 
The NPRM proposed to require one time high and low frequency eddy 
current inspections of the affected fuselage skin for cracks, and 
repair if necessary. We are issuing this AD to detect and correct 
cracks in the fuselage skin; such cracking could result in reduced 
structural integrity of the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive Airworthiness Directive 2016-0029R1, dated 
November 17, 2016 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Fokker Services B.V. Model F28 Mark 0100 
airplanes. The MCAI states:

    A complementary fatigue and damage tolerance analysis was 
accomplished by the design approval holder on the traffic collision 
avoidance system (TCAS) antenna installation on the top of the 
fuselage between station (STA) 6805 and STA7305. Based on the 
results, it was determined that for the affected area, the current 
58 000 flight cycles (FC) threshold of Airworthiness Limitations 
Section (ALS) inspection task 533001-00-20 and 533028-00-20 (special 
detailed inspection of longitudinal lap joints) is insufficient to 
timely detect possible crack development.
    This condition, if not detected and corrected, could affect the 
structural integrity of the fuselage in this area.
    To address this potential unsafe condition, Fokker Services 
published Service Bulletin (SB) SBF100-53-130 to provide inspection 
instructions.
    Consequently, EASA issued AD 2016-0029 to require a one-time 
inspection of the fuselage skin around the largest TCAS antenna 
external doubler and of the longitudinal lap joint at stringer (STR) 
37 between fuselage STA6805 and STA7305.
    Since that [EASA] AD was issued, it was discovered that another 
ALS inspection task, 533028-00-20, is also related to this subject. 
This [EASA] AD is revised to clarify that the inspection threshold 
of both ALS inspection tasks has been re-assessed. It is expected 
that a repetitive inspection task will be included in the ALS, which 
will cover only the area close to the TCAS antenna installation. For 
the remainder of the affected lap joint, no change is anticipated 
and this will therefore continue to be inspected in accordance with 
the existing ALS tasks.
    This [EASA] AD is still considered to be an interim action and 
further [EASA] AD

[[Page 5366]]

action may follow. More information on this subject can be found in 
Fokker Services All Operators Message AOF100.199#02.

    You may examine the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9058.

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.

Revised MCAI AD

    Since the NPRM was issued, EASA revised 2016-0029, dated March 8, 
2016. EASA AD 2016-0029R1, dated November 17, 2016, clarifies that the 
inspection threshold of both ALS inspection tasks have been re-
assessed. The revised MCAI did not result in a change to the NPRM. We 
have revised this AD to refer to EASA AD 2016-0029R1, dated November 
17, 2016.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    We reviewed Fokker Service Bulletin SBF100-53-130, dated December 
1, 2015. This service information describes one time high and low 
frequency eddy current inspections for cracks of the fuselage skin. 
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 per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  1 work-hour x $85 per                 $0             $85            $680
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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):

2017-01-04 Fokker Services B.V.: Amendment 39-18771; Docket No. FAA-
2016-9058; Directorate Identifier 2016-NM 024-AD.

(a) Effective Date

    This AD is effective February 22, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Fokker Services B.V. Model F28 Mark 0100 
airplanes, certificated in any category, serial numbers 11244 
through 11407 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by an analysis which determined that, for 
certain areas of the fuselage, the current threshold of an 
Airworthiness Limitations Section inspection is insufficient to 
detect early crack development. We are issuing this AD to detect and 
correct cracks in the fuselage skin; such cracking could result in 
reduced structural integrity of the fuselage.

(f) Compliance

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

(g) Inspection

    Within the compliance time specified in paragraphs (g)(1) and 
(g)(2) of this AD, as applicable, do high and low frequency eddy 
current inspections for cracks in the fuselage skin around the 
largest traffic collision avoidance system (TCAS) antenna external 
doubler and of the longitudinal lap joint at

[[Page 5367]]

fuselage stringer STR37 between fuselage station (STA) STA6805 and 
STA7305, in accordance with the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-53-130, dated December 1, 2015.
    (1) For airplanes having 45,000 or more total flight cycles as 
of the effective date of this AD, since the date of issuance of the 
original airworthiness certificate or the date of issuance of the 
original export certificate of airworthiness: Do the high and low 
frequency eddy current inspections within 750 flight cycles after 
the effective date of this AD.
    (2) For airplanes having 40,000 or more total flight cycles, but 
less than 45,000 total flight cycles as of the effective date of 
this AD, since the date of issuance of the original airworthiness 
certificate or the date of issuance of the original export 
certificate of airworthiness: Do the high and low frequency eddy 
current inspections within 1,500 flight cycles after the effective 
date of this AD.

(h) Corrective Action

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, 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 B.V. Service's EASA Design Organization 
Approval (DOA).

(i) 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: <a href="/cdn-cgi/l/email-protection#5f66721e1112726e6e69721e12101c720d1a0e0a1a0c0b0c1f393e3e71383029"><span class="__cf_email__" data-cfemail="d6effb97989bfbe7e7e0fb979b9995fb849387839385828596b0b7b7f8b1b9a0">[email&#160;protected]</span></a>. 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 EASA; or 
Fokker Services B.V.'s EASA DOA. If approved by the DOA, the 
approval must include the DOA-authorized signature.

(j) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2016-0029R1, dated November 17, 2016, for related 
information. This MCAI may be found in the AD docket on the Internet 
at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket 
No. FAA-2016-9058.

(k) 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 SBF100-53-130, dated December 1, 
2015.
    (ii) Reserved.
    (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: <a href="/cdn-cgi/l/email-protection#e29687818a8c8b81838e918790948b818791a2848d89898790cc818d8f"><span class="__cf_email__" data-cfemail="661203050e080f05070a150314100f0503152600090d0d03144805090b">[email&#160;protected]</span></a>; Internet 
<a href="http://www.myfokkerfleet.com">http://www.myfokkerfleet.com</a>.
    (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.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on December 27, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-00410 Filed 1-17-17; 8:45 am]
 BILLING CODE 4910-13-P