83 FR 1532 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 9 (January 12, 2018)

Page Range		1532-1535
FR Document		2018-00339

We are superseding Airworthiness Directive (AD) 95-25-02, which applied to certain Fokker Services B.V. Model F28 Mark 0100 airplanes. AD 95-25-02 required inspection(s) to detect cracks of the fuselage-mounted half of hinge assemblies of the small cargo door, and replacement of any cracked hinge assembly with a new hinge assembly. This new AD was prompted by a report that the hinges of the small cargo door are made of a material that is sensitive to stress corrosion and fatigue cracking, and by the determination that the existing inspection program does not provide sufficient protection against fatigue-induced cracks. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products.

Federal Register, Volume 83 Issue 9 (Friday, January 12, 2018)

[Federal Register Volume 83, Number 9 (Friday, January 12, 2018)]
[Rules and Regulations]
[Pages 1532-1535]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2018-00339]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1242; Product Identifier 2013-NM-043-AD; Amendment
39-19150; AD 2018-01-09]
RIN 2120-AA64

Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 95-25-02,
which applied to certain Fokker Services B.V. Model F28 Mark 0100

[[Page 1533]]

airplanes. AD 95-25-02 required inspection(s) to detect cracks of the
fuselage-mounted half of hinge assemblies of the small cargo door, and
replacement of any cracked hinge assembly with a new hinge assembly.
This new AD was prompted by a report that the hinges of the small cargo
door are made of a material that is sensitive to stress corrosion and
fatigue cracking, and by the determination that the existing inspection
program does not provide sufficient protection against fatigue-induced
cracks. This AD requires contacting the FAA to obtain instructions for
addressing the unsafe condition on these products, and doing the
actions specified in those instructions. We are issuing this AD to
address the unsafe condition on these products.

DATES: This AD becomes effective January 29, 2018.
We must receive comments on this AD by February 26, 2018.

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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.

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-2017-
1242; or in person at the Docket Operations office 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 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 Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1137; fax: 425-
227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

We issued AD 95-25-02, Amendment 39-9446 (60 FR 63615, December 12,
1995) (``AD 95-25-02''), which applied to certain Fokker Services B.V.
Model F28 Mark 0100 airplanes. AD 95-25-02 was prompted by a report
that the hinges of the small cargo door are made of a material that is
sensitive to stress corrosion cracking. AD 95-25-02 required
inspection(s) to detect cracks of the fuselage-mounted half of hinge
assemblies of the small cargo door, and replacement of any cracked
hinge assembly with a new hinge assembly. We issued AD 95-25-02 to
prevent failure of the hinges of the small cargo door due to stress
corrosion cracking, which could result in opening and/or separation of
the door while the airplane is in flight, and resultant rapid
decompression and/or structural damage to the airplane.
Since we issued AD 95-25-02, we have determined that the existing
inspection program does not provide sufficient protection against
fatigue-induced cracks.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2013-0028, dated February 8, 2013 (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:

Over the years, stress corrosion- and fatigue-induced cracks
were found on the hinges of the downward opening small cargo doors
installed on Fokker F28 Mark 0100 aeroplanes.
To address the potential unsafe condition with respect to stress
corrosion, CAA-NL issued AD (BLA) 93-036/2 [which corresponded to
FAA AD 95-25-02] to require repetitive inspections and, if cracks
are found, replacement of the hinges with hinges of a new design.
These new hinges were installed before delivery on aeroplanes with
s/n 11409 and higher.
To ensure the continued structural integrity with respect to
fatigue, a repetitive inspection was included in the Airworthiness
Limitations Section (ALS) of the Instructions for Continued
Airworthiness.
As part of the Widespread Fatigue Damage re-evaluation, it was
concluded that the repetitive fatigue inspection in the ALS does not
provide a sufficient level of protection against the fatigue-induced
cracks.
For the reasons described above, this [EASA] AD retains the
requirements of CAA-NL AD 93-036/2, which is superseded, and
requires replacement of Part Number (P/N) A28410-405 and P/N A28410-
407 hinges with modified P/N D28410-409 hinges.

You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1242.

FAA's Determination and Requirements of This 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. We are
issuing this AD because we evaluated all pertinent information and
determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.

FAA's Determination of the Effective Date

Since there are currently no domestic operators of this product, we
find good cause that notice and opportunity for prior public comment
are unnecessary. In addition, for the reason(s) stated above, we find
that good cause exists for making this amendment effective in less than
30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2017-1242; Product
Identifier 2013-NM-043-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

Currently, there are no affected U.S.-registered airplanes. This AD
requires contacting the FAA to obtain instructions for addressing the
unsafe condition, and doing the actions specified in those
instructions. Based on the actions specified in the MCAI AD,

[[Page 1534]]

we are providing the following cost estimates for an affected airplane
that is placed on the U.S. Register in the future:

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions from 2 work-hours x $85 per hour $0.................... $170 per inspection
AD 95-25-02). = $170 per inspection cycle.
cycle.
Replacement (new action)........... Up to 186 work-hours x $85 Up to $7,700.......... Up to $23,510.
per hour = $15,810.
----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary on-condition
replacements that would be required based on the results of the
required actions:

On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement (retained actions from Up to 186 work-hours x $85 Up to $7,700.......... Up to $23,510.
AD 95-25-02). per hour = $15,810.
----------------------------------------------------------------------------------------------------------------

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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.

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 removing airworthiness directive (AD)
95-25-02, Amendment 39-9446 (60 FR 63617, December 12, 1995), and
adding the following new AD:

2018-01-09 Fokker Services B.V.: Amendment 39-19150; Docket No. FAA-
2017-1242; Product Identifier 2013-NM-043-AD.

(a) Effective Date

This AD becomes effective January 29, 2018.

(b) Affected ADs

This AD replaces AD 95-25-02, Amendment 39-9446 (60 FR 63615,
December 12, 1995) (``AD 95-25-02'').

This AD applies to Fokker Services B.V. Model F28 Mark 0100
series airplanes, certificated in any category, serial numbers 11244
through 11267 inclusive, 11284, 11285, 11287, 11288, 11290, 11292,
11294, 11296, 11298, 11299, 11301, 11302, 11304, 11305, 11307,
11309, 11311, 11315, 11317, 11319, 11320, 11322, 11336, 11339, 11341
through 11344 inclusive, 11347, 11348, 11350, 11351, 11362 through
11364 inclusive, 11371, 11374, 11375, 11381 through 11384 inclusive,
11386, 11389, 11390, 11394, and 11401.

(d) Subject

Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

This AD was prompted by a report that the hinges of the small
cargo door are made of a material that is sensitive to stress
corrosion cracking, and by the determination that the existing
inspection program does not provide sufficient protection against
fatigue-induced cracks. We are issuing this AD to prevent failure of
the hinges of the small cargo door due to stress corrosion cracking,
which could result in opening and/or separation of the door while
the airplane is in flight, and resultant rapid decompression and/or
structural damage to the airplane.

(f) Compliance

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

[[Page 1535]]

(g) Required Action(s)

Within 30 days after the effective date of this AD, request
instructions from the Manager, International Section, Transport
Standards Branch, FAA, to address the unsafe condition specified in
paragraph (e) of this AD; and accomplish the action(s) at the times
specified in, and in accordance with, those instructions. Guidance
can be found in Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) AD 2013-0028, dated
February 8, 2013.

(h) Alternative Methods of Compliance (AMOCs)

The Manager, International Section, Transport Standards Branch,
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 Section, send it to the
attention of the person identified in paragraph (i)(2) of this AD.
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office.

(i) Related Information

(1) Refer to MCAI EASA AD 2013-0028, dated February 8, 2013, for
related information. You may examine the MCAI on the internet at
http://www.regulations.gov by searching for and locating Docket No.
FAA-2017-1242.
(2) For more information about this AD, contact Tom Rodriguez,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone:
425-227-1137; fax: 425-227-1149.

(j) Material Incorporated by Reference

None.

Issued in Renton, Washington, on January 2, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-00339 Filed 1-11-18; 8:45 am]
BILLING CODE 4910-13-P

1532 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations

(ii) Part II of the Accomplishment (j) Follow-On Inspection for Interim Airframe Section, FAA, Los Angeles ACO
Instructions of Boeing Alert Service Bulletin Modification and Repair Branch, 3960 Paramount Boulevard,
737–53A1166, Revision 1, dated May 25, For airplanes having line numbers 1 Lakewood, CA 90712–4137; phone: 562–627–
1995. through 3132 inclusive, on which an interim 5232; fax: 562–627–5210; email:
(iii) Part II of the Accomplishment modification of the BS 727 outboard chord as george.garrido@faa.gov.
Instructions of Boeing Alert Service Bulletin defined in part 6 of the Accomplishment (n) Material Incorporated by Reference
737–53A1166, dated June 30, 1994. Instructions of Boeing Alert Service Bulletin
(4) Airplanes on which the outboard chord 737–53A1166, Revision 2, dated May 25, (1) The Director of the Federal Register
has not been replaced in accordance with the 2006, has been accomplished: Within 60,000 approved the incorporation by reference
method specified in paragraph (h)(4)(i), flight cycles after accomplishment of the (IBR) of the service information listed in this
interim modification of the outboard chord of paragraph under 5 U.S.C. 552(a) and 1 CFR
(h)(4)(ii), or (h)(4)(iii) of this AD.
the frame at BS 727 at S–18A, but no earlier part 51.
(i) Part 3 of the Accomplishment
than 50,000 flight cycles after (2) You must use this service information
Instructions of Boeing Alert Service Bulletin
accomplishment of the modification, do a as applicable to do the actions required by
737–53A1166, Revision 2, dated May 25,
one-time follow-on open-hole eddy current this AD, unless the AD specifies otherwise.
2006. (3) The following service information was
inspection to detect cracks in the modified
(ii) Part I of the Accomplishment approved for IBR on December 26, 2012 (77
chord, in accordance with part 8 of the
Instructions of Boeing Alert Service Bulletin FR 69747, November 21, 2012).
Accomplishment Instructions of Boeing Alert
737–53A1166, Revision 1, dated May 25, Service Bulletin 737–53A1166, Revision 2, (i) Boeing Alert Service Bulletin 737–
1995. dated May 25, 2006. If any crack is found 53A1166, Revision 2, dated May 25, 2006.
(iii) Part I of the Accomplishment during the inspection required by this (ii) Reserved.
Instructions of Boeing Alert Service Bulletin paragraph, before further flight, repair in (4) For service information identified in
737–53A1166, dated June 30, 1994. accordance with part 3 or part 4, as this AD, contact Boeing Commercial
(i) Edge Margin Measurement, Related applicable, of the Accomplishment Airplanes, Attention: Contractual & Data
Instructions of Boeing Alert Service Bulletin Services (C&DS), 2600 Westminster Blvd.,
Investigative Actions, and Repair
737–53A1166, Revision 2, dated May 25, MC 110–SK57, Seal Beach, CA 90740;
For Model 737–100, –200, and –200C 2006; except, where the repairs cannot be telephone 562–797–1717; internet https://
series airplanes having line numbers 1 installed using the procedures identified in www.myboeingfleet.com.
through 999 inclusive, identified as Groups this service bulletin, repair before further (5) You may view this service information
1 through 3 in Boeing Alert Service Bulletin flight using a method approved in at the FAA, Transport Standards Branch,
737–53A1166, Revision 2, dated May 25, accordance with the procedures specified in 1601 Lind Avenue SW, Renton, WA. For
2006, on which the preventive modification paragraph (l) of this AD. information on the availability of this
has been installed in accordance with Boeing (k) Exception to the Service Information material at the FAA, call 425–227–1221.
Alert Service Bulletin 737–53A1166, dated (6) You may view this service information
June 30, 1994; or Boeing Alert Service Access and restoration procedures that is incorporated by reference at the
Bulletin 737–53A1166, Revision 1, dated specified in the Accomplishment National Archives and Records
Instructions of Boeing Alert Service Bulletin Administration (NARA). For information on
May 25, 1995: Within 60,000 flight cycles
737–53A1166, Revision 2, dated May 25, the availability of this material at NARA, call
after accomplishing the preventive
2006, are not required by this AD. Operators
modification, determine if the modification is 202–741–6030, or go to: http://
may do those actions following their
classified as interim or permanent by using www.archives.gov/federal-register/cfr/ibr-
approved maintenance procedures.
the edge margin measurement classification locations.html.
specified in part 6 of the Accomplishment (l) Alternative Methods of Compliance Issued in Renton, Washington, on January
Instructions of Boeing Alert Service Bulletin (AMOCs) 2, 2018.
737–53A1166, Revision 2, dated May 25, (1) The Manager, Los Angeles ACO Branch, Michael Kaszycki,
2006. In lieu of measuring on the airplane, FAA, has the authority to approve AMOCs
a review of engineering documentation may Acting Director, System Oversight Division,
for this AD, if requested using the procedures
be used to classify the modification if the found in 14 CFR 39.19. In accordance with Aircraft Certification Service.
engineering documentation was completed at 14 CFR 39.19, send your request to your [FR Doc. 2018–00256 Filed 1–11–18; 8:45 am]
the time of the modification and has the edge principal inspector or local Flight Standards BILLING CODE 4910–13–P
margins recorded. District Office, as appropriate. If sending
(1) If the modification is classified as information directly to the manager of the
permanent, no further action is required by certification office, send it to the attention of DEPARTMENT OF TRANSPORTATION
paragraph (i) of this AD. the person identified in paragraph (m) of this
(2) If the modification is classified as AD. Information may be emailed to: 9-ANM- Federal Aviation Administration
interim: Within 60,000 flight cycles after LAACO-AMOC-Requests@faa.gov.
accomplishment of the interim modification (2) Before using any approved AMOC,
14 CFR Part 39
of the outboard chord of the frame at BS 727 notify your appropriate principal inspector,
at S–18A, but no earlier than 50,000 flight or lacking a principal inspector, the manager [Docket No. FAA–2017–1242; Product
cycles after accomplishment of the of the local flight standards district office/ Identifier 2013–NM–043–AD; Amendment
modification, do a one-time follow-on open- certificate holding district office. 39–19150; AD 2018–01–09]
hole eddy current inspection to detect cracks (3) An AMOC that provides an acceptable
level of safety may be used for any repair, RIN 2120–AA64
in the modified chord, in accordance with
modification, or alteration required by this
part 8 of the Accomplishment Instructions of
AD if it is approved by the Boeing Airworthiness Directives; Fokker
Boeing Alert Service Bulletin 737–53A1166,
Commercial Airplanes Organization Services B.V. Airplanes
Revision 2, dated May 25, 2006. If any crack Designation Authorization (ODA) that has
is found, before further flight, repair in been authorized by the Manager, Los Angeles AGENCY: Federal Aviation
accordance with part 3 or part 4, as ACO Branch, to make those findings. To be Administration (FAA), DOT.
sradovich on DSK3GMQ082PROD with RULES

applicable, of the Accomplishment approved, the repair method, modification
Instructions of Boeing Alert Service Bulletin ACTION: Final rule; request for
deviation, or alteration deviation must meet
737–53A1166, Revision 2, dated May 25, the certification basis of the airplane, and the comments.
2006; except, if the repairs cannot be approval must specifically refer to this AD.
installed using the identified procedures, SUMMARY: We are superseding
repair before further flight using a method (m) Related Information Airworthiness Directive (AD) 95–25–02,
approved in accordance with the procedures For more information about this AD, which applied to certain Fokker
specified in paragraph (l) of this AD. contact George Garrido, Aerospace Engineer, Services B.V. Model F28 Mark 0100

VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1

Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 1533

airplanes. AD 95–25–02 required telephone: 425–227–1137; fax: 425– A28410–405 and P/N A28410–407 hinges
inspection(s) to detect cracks of the 227–1149. with modified P/N D28410–409 hinges.
fuselage-mounted half of hinge SUPPLEMENTARY INFORMATION: You may examine the MCAI on the
assemblies of the small cargo door, and internet at http://www.regulations.gov
replacement of any cracked hinge Discussion
by searching for and locating Docket No.
assembly with a new hinge assembly. We issued AD 95–25–02, Amendment FAA–2017–1242.
This new AD was prompted by a report 39–9446 (60 FR 63615, December 12,
that the hinges of the small cargo door 1995) (‘‘AD 95–25–02’’), which applied FAA’s Determination and Requirements
are made of a material that is sensitive to certain Fokker Services B.V. Model of This AD
to stress corrosion and fatigue cracking, F28 Mark 0100 airplanes. AD 95–25–02 This product has been approved by
and by the determination that the was prompted by a report that the the aviation authority of another
existing inspection program does not hinges of the small cargo door are made country, and is approved for operation
provide sufficient protection against of a material that is sensitive to stress in the United States. Pursuant to our
fatigue-induced cracks. This AD corrosion cracking. AD 95–25–02 bilateral agreement with the State of
requires contacting the FAA to obtain required inspection(s) to detect cracks of Design Authority, we have been notified
instructions for addressing the unsafe the fuselage-mounted half of hinge of the unsafe condition described in the
condition on these products, and doing assemblies of the small cargo door, and MCAI. We are issuing this AD because
the actions specified in those replacement of any cracked hinge we evaluated all pertinent information
instructions. We are issuing this AD to assembly with a new hinge assembly. and determined the unsafe condition
address the unsafe condition on these We issued AD 95–25–02 to prevent exists and is likely to exist or develop
products. failure of the hinges of the small cargo on other products of the same type
door due to stress corrosion cracking, design.
DATES: This AD becomes effective
which could result in opening and/or FAA’s Determination of the Effective
January 29, 2018.
separation of the door while the Date
We must receive comments on this airplane is in flight, and resultant rapid
AD by February 26, 2018. decompression and/or structural Since there are currently no domestic
ADDRESSES: You may send comments, damage to the airplane. operators of this product, we find good
using the procedures found in 14 CFR Since we issued AD 95–25–02, we cause that notice and opportunity for
11.43 and 11.45, by any of the following have determined that the existing prior public comment are unnecessary.
methods: inspection program does not provide In addition, for the reason(s) stated
• Federal eRulemaking Portal: Go to sufficient protection against fatigue- above, we find that good cause exists for
http://www.regulations.gov. Follow the induced cracks. making this amendment effective in less
instructions for submitting comments. The European Aviation Safety Agency than 30 days.
• Fax: 202–493–2251. (EASA), which is the Technical Agent Comments Invited
• Mail: U.S. Department of for the Member States of the European
Union, has issued EASA AD 2013–0028, This AD is a final rule that involves
Transportation, Docket Operations, M–
dated February 8, 2013 (referred to after requirements affecting flight safety, and
30, West Building Ground Floor, Room
this as the Mandatory Continuing we did not precede it by notice and
W12–140, 1200 New Jersey Avenue SE,
Airworthiness Information, or ‘‘the opportunity for public comment. We
Washington, DC 20590.
invite you to send any written relevant
• Hand Delivery: U.S. Department of MCAI’’), to correct an unsafe condition
for certain Fokker Services B.V. Model data, views, or arguments about this AD.
Transportation, Docket Operations, M–
F28 Mark 0100 airplanes. The MCAI Send your comments to an address
30, West Building Ground Floor, Room
states: listed under the ADDRESSES section.
W12–140, 1200 New Jersey Avenue SE,
Include ‘‘Docket No. FAA–2017–1242;
Washington, DC, between 9 a.m. and 5 Over the years, stress corrosion- and
Product Identifier 2013–NM–043–AD’’
p.m., Monday through Friday, except fatigue-induced cracks were found on the
hinges of the downward opening small cargo at the beginning of your comments. We
Federal holidays.
doors installed on Fokker F28 Mark 0100 specifically invite comments on the
Examining the AD Docket aeroplanes. overall regulatory, economic,
To address the potential unsafe condition environmental, and energy aspects of
You may examine the AD docket on with respect to stress corrosion, CAA–NL this AD. We will consider all comments
the internet at http:// issued AD (BLA) 93–036/2 [which received by the closing date and may
www.regulations.gov by searching for corresponded to FAA AD 95–25–02] to amend this AD based on those
and locating Docket No. FAA–2017– require repetitive inspections and, if cracks
comments.
1242; or in person at the Docket are found, replacement of the hinges with
We will post all comments we
Operations office between 9 a.m. and 5 hinges of a new design. These new hinges
were installed before delivery on aeroplanes receive, without change, to http://
p.m., Monday through Friday, except www.regulations.gov, including any
Federal holidays. The AD docket with s/n 11409 and higher.
To ensure the continued structural personal information you provide. We
contains this AD, the regulatory will also post a report summarizing each
integrity with respect to fatigue, a repetitive
evaluation, any comments received, and inspection was included in the substantive verbal contact we receive
other information. The street address for Airworthiness Limitations Section (ALS) of about this AD.
the Docket Operations office (telephone: the Instructions for Continued Airworthiness.
800–647–5527) is in the ADDRESSES As part of the Widespread Fatigue Damage Costs of Compliance
sradovich on DSK3GMQ082PROD with RULES

section. Comments will be available in re-evaluation, it was concluded that the Currently, there are no affected U.S.-
the AD docket shortly after receipt. repetitive fatigue inspection in the ALS does
registered airplanes. This AD requires
not provide a sufficient level of protection
FOR FURTHER INFORMATION CONTACT: Tom
against the fatigue-induced cracks. contacting the FAA to obtain
Rodriguez, Aerospace Engineer, For the reasons described above, this instructions for addressing the unsafe
International Section, Transport [EASA] AD retains the requirements of CAA– condition, and doing the actions
Standards Branch, FAA, 1601 Lind NL AD 93–036/2, which is superseded, and specified in those instructions. Based on
Avenue SW, Renton, WA 98057–3356; requires replacement of Part Number (P/N) the actions specified in the MCAI AD,

VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1

1534 Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations

we are providing the following cost estimates for an affected airplane that is
placed on the U.S. Register in the future:

ESTIMATED COSTS
Action Labor cost Parts cost Cost per product

Inspections (retained actions from AD 95–25– 2 work-hours × $85 per hour = $170 per in- $0 ............................... $170 per inspection
02). spection cycle. cycle.
Replacement (new action) ............................... Up to 186 work-hours × $85 per hour = Up to $7,700 .............. Up to $23,510.
$15,810.

We estimate the following costs to do based on the results of the required
any necessary on-condition actions:
replacements that would be required

ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product

Replacement (retained actions from AD 95– Up to 186 work-hours × $85 per hour = Up to $7,700 .............. Up to $23,510.
25–02). $15,810.

Authority for This Rulemaking the national government and the States, FAA–2017–1242; Product Identifier
or on the distribution of power and 2013–NM–043–AD.
Title 49 of the United States Code
specifies the FAA’s authority to issue responsibilities among the various (a) Effective Date
rules on aviation safety. Subtitle I, levels of government. This AD becomes effective January 29,
section 106, describes the authority of For the reasons discussed above, I 2018.
the FAA Administrator. ‘‘Subtitle VII: certify that this AD:
1. Is not a ‘‘significant regulatory (b) Affected ADs
Aviation Programs,’’ describes in more
action’’ under Executive Order 12866; This AD replaces AD 95–25–02,
detail the scope of the Agency’s 2. Is not a ‘‘significant rule’’ under the Amendment 39–9446 (60 FR 63615,
authority. DOT Regulatory Policies and Procedures December 12, 1995) (‘‘AD 95–25–02’’).
We are issuing this rulemaking under (44 FR 11034, February 26, 1979);
the authority described in ‘‘Subtitle VII, (c) Applicability
3. Will not affect intrastate aviation in
Part A, Subpart III, Section 44701: This AD applies to Fokker Services B.V.
Alaska; and Model F28 Mark 0100 series airplanes,
General requirements.’’ Under that 4. Will not have a significant
section, Congress charges the FAA with certificated in any category, serial numbers
economic impact, positive or negative, 11244 through 11267 inclusive, 11284,
promoting safe flight of civil aircraft in on a substantial number of small entities 11285, 11287, 11288, 11290, 11292, 11294,
air commerce by prescribing regulations under the criteria of the Regulatory 11296, 11298, 11299, 11301, 11302, 11304,
for practices, methods, and procedures Flexibility Act. 11305, 11307, 11309, 11311, 11315, 11317,
the Administrator finds necessary for 11319, 11320, 11322, 11336, 11339, 11341
safety in air commerce. This regulation List of Subjects in 14 CFR Part 39 through 11344 inclusive, 11347, 11348,
is within the scope of that authority Air transportation, Aircraft, Aviation 11350, 11351, 11362 through 11364
because it addresses an unsafe condition safety, Incorporation by reference, inclusive, 11371, 11374, 11375, 11381
that is likely to exist or develop on through 11384 inclusive, 11386, 11389,
Safety.
11390, 11394, and 11401.
products identified in this rulemaking
action. Adoption of the Amendment (d) Subject
This AD is issued in accordance with Accordingly, under the authority Air Transport Association (ATA) of
authority delegated by the Executive delegated to me by the Administrator, America Code 52, Doors.
Director, Aircraft Certification Service, the FAA amends 14 CFR part 39 as
(e) Reason
as authorized by FAA Order 8000.51C. follows:
In accordance with that order, issuance This AD was prompted by a report that the
PART 39—AIRWORTHINESS hinges of the small cargo door are made of
of ADs is normally a function of the
DIRECTIVES a material that is sensitive to stress corrosion
Compliance and Airworthiness cracking, and by the determination that the
Division, but during this transition existing inspection program does not provide
■ 1. The authority citation for part 39
period, the Executive Director has sufficient protection against fatigue-induced
continues to read as follows:
delegated the authority to issue ADs cracks. We are issuing this AD to prevent
applicable to transport category Authority: 49 U.S.C. 106(g), 40113, 44701. failure of the hinges of the small cargo door
airplanes to the Director of the System due to stress corrosion cracking, which could
§ 39.13 [Amended]
Oversight Division. result in opening and/or separation of the
sradovich on DSK3GMQ082PROD with RULES

■ 2. The FAA amends § 39.13 by door while the airplane is in flight, and
Regulatory Findings removing airworthiness directive (AD) resultant rapid decompression and/or
95–25–02, Amendment 39–9446 (60 FR structural damage to the airplane.
We determined that this AD will not
have federalism implications under 63617, December 12, 1995), and adding (f) Compliance
Executive Order 13132. This AD will the following new AD: Comply with this AD within the
not have a substantial direct effect on 2018–01–09 Fokker Services B.V.: compliance times specified, unless already
the States, on the relationship between Amendment 39–19150; Docket No. done.

VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1

Federal Register / Vol. 83, No. 9 / Friday, January 12, 2018 / Rules and Regulations 1535

(g) Required Action(s) DEPARTMENT OF TRANSPORTATION 1243; or in person at the Docket
Within 30 days after the effective date of Operations office between 9 a.m. and 5
this AD, request instructions from the Federal Aviation Administration p.m., Monday through Friday, except
Manager, International Section, Transport Federal holidays. The AD docket
Standards Branch, FAA, to address the 14 CFR Part 39 contains this AD, the regulatory
unsafe condition specified in paragraph (e) of [Docket No. FAA–2017–1243; Product evaluation, any comments received, and
this AD; and accomplish the action(s) at the Identifier 2012–NM–150–AD; Amendment other information. The street address for
times specified in, and in accordance with, 39–19151; AD 2018–01–10] the Docket Operations office (telephone:
those instructions. Guidance can be found in 800–647–5527) is in the ADDRESSES
RIN 2120–AA64
Mandatory Continuing Airworthiness section. Comments will be available in
Information (MCAI) European Aviation Airworthiness Directives; Airbus the AD docket shortly after receipt.
Safety Agency (EASA) AD 2013–0028, dated Airplanes FOR FURTHER INFORMATION CONTACT:
February 8, 2013. Vladimir Ulyanov, Aerospace Engineer,
AGENCY: Federal Aviation International Section, Transport
(h) Alternative Methods of Compliance
(AMOCs)
Administration (FAA), DOT. Standards Branch, FAA, 1601 Lind
ACTION: Final rule; request for Avenue SW, Renton, WA 98057–3356;
The Manager, International Section,
comments. telephone: 425–227–1138; fax: 425–
Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if
227–1149.
SUMMARY: We are superseding
requested using the procedures found in 14 SUPPLEMENTARY INFORMATION:
Airworthiness Directive (AD) 2011–14–
CFR 39.19. In accordance with 14 CFR 39.19, 10, which applied to certain Airbus Discussion
send your request to your principal inspector Model A330–342 airplanes. AD 2011–
or local Flight Standards District Office, as We issued AD 2011–14–10,
14–10 required repetitive ultrasonic Amendment 39–16745 (76 FR 41657,
appropriate. If sending information directly inspections for cracks of a certain
to the International Section, send it to the July 15, 2011) (‘‘AD 2011–14–10’’),
fuselage frame at the fastener hole area which applied to certain Airbus Model
attention of the person identified in just above a certain stringer, and repair,
paragraph (i)(2) of this AD. Information may A330–342 airplanes. AD 2011–14–10
if necessary. This new AD was was prompted by a determination that
be emailed to: 9-ANM-116-AMOC-
prompted by a new fatigue and damage airworthiness limitation item (ALI) task
REQUESTS@faa.gov. Before using any
tolerance evaluation, which showed that 533105–10–02 was not performed on
approved AMOC, notify your appropriate
certain inspection thresholds and certain airplanes. AD 2011–14–10
principal inspector, or lacking a principal
intervals need to be shorter. This AD required repetitive ultrasonic
inspector, the manager of the local flight
requires contacting the FAA to obtain inspections for cracks of fuselage frame
standards district office/certificate holding
instructions for addressing the unsafe 39.1 at the fastener hole area just above
district office.
condition on these products, and doing stringer 28, and repair, if necessary. We
(i) Related Information the actions specified in those issued AD 2011–14–10 to detect and
(1) Refer to MCAI EASA AD 2013–0028, instructions. We are issuing this AD to correct fatigue cracking of the internal
dated February 8, 2013, for related address the unsafe condition on these structure of the fuselage, which could
information. You may examine the MCAI on products. adversely affect the structural integrity
the internet at http://www.regulations.gov by DATES: This AD becomes effective of the airplane.
searching for and locating Docket No. FAA– January 29, 2018. Since we issued AD 2011–14–10, we
2017–1242. We must receive comments on this have determined, based on a new
(2) For more information about this AD, AD by February 26, 2018. fatigue and damage tolerance evaluation
contact Tom Rodriguez, Aerospace Engineer, that took into account airplane usage,
ADDRESSES: You may send comments,
International Section, Transport Standards that the compliance time threshold and
using the procedures found in 14 CFR
Branch, FAA, 1601 Lind Avenue SW, intervals need to be shorter.
11.43 and 11.45, by any of the following
Renton, WA 98057–3356; telephone: 425– The European Aviation Safety Agency
methods:
227–1137; fax: 425–227–1149.
• Federal eRulemaking Portal: Go to (EASA), which is the Technical Agent
(j) Material Incorporated by Reference http://www.regulations.gov. Follow the for the Member States of the European
None. instructions for submitting comments. Union, has issued EASA AD 2012–0140,
• Fax: 202–493–2251. dated July 27, 2012 (referred to after this
Issued in Renton, Washington, on January • Mail: U.S. Department of as the Mandatory Continuing
2, 2018. Transportation, Docket Operations, M– Airworthiness Information, or ‘‘the
Michael Kaszycki, 30, West Building Ground Floor, Room MCAI’’), to correct an unsafe condition
Acting Director, System Oversight Division, W12–140, 1200 New Jersey Avenue SE, for certain Airbus Model A330–342
Aircraft Certification Service. Washington, DC 20590. airplanes. The MCAI states:
[FR Doc. 2018–00339 Filed 1–11–18; 8:45 am] • Hand Delivery: U.S. Department of Airworthiness Limitation Item (ALI) task
BILLING CODE 4910–13–P Transportation, Docket Operations, M– 533105–01–02 is applicable to aeroplanes on
30, West Building Ground Floor, Room which Airbus modification 40391 has not
W12–140, 1200 New Jersey Avenue SE, been embodied in production. The
Washington, DC, between 9 a.m. and 5 requirements associated to this task are
p.m., Monday through Friday, except applicable to aeroplanes on which
sradovich on DSK3GMQ082PROD with RULES

Modification Proposal (MP) S10374 has not
Federal holidays.
been embodied.
Examining the AD Docket Following a query from an operator,
investigations revealed that some aeroplane
You may examine the AD docket on [manufacturer serial numbers] MSN, for
the internet at http:// which Airbus modification 40391 was
www.regulations.gov by searching for indicated as fully embodied inside the
and locating Docket No. FAA–2017– Aircraft Inspection Report (AIR), did not

VerDate Sep<11>2014 15:52 Jan 11, 2018 Jkt 244001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\12JAR1.SGM 12JAR1

Document Created: 2018-10-26 09:53:40
Document Modified: 2018-10-26 09:53:40

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		Rules and Regulations
Action		Final rule; request for comments.
Dates		This AD becomes effective January 29, 2018.
Contact		Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1137; fax: 425- 227-1149.
FR Citation		83 FR 1532
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

83 FR 1532 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 9 (January 12, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration