Airworthiness Directives; Fokker Services B.V. Airplanes, 64057-64060 [2016-22186]
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Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations
(m) Life Limit for P/N C2CF619A
As of October 24, 2016 (the effective date
of this AD), elevator control rod assemblies,
P/N C2CF619A, are life-limited to 15 years
and must be replaced with P/N C2CF619A–
11, which is not a life-limited part, at the
following compliance time:
(1) If, as of October 24, 2016 (the effective
date of this AD), the age of the installed P/
N C2CF619A is known, it must be replaced
before exceeding the life limit or within the
next 12 months after October 24, 2016 (the
effective date of this AD), whichever occurs
later.
(2) If, as of October 24, 2016 (the effective
date of this AD), the age of the installed P/
N C2CF619A is not known, it must be
replaced within the next 12 months after
October 24, 2016 (the effective date of this
AD).
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(n) Credit for Actions Accomplished in
Accordance With Previous Service
Information
Credit will be given for the inspections
required in paragraphs (g)(1) through (3) of
this AD if they were done before October 24,
2016 (the effective date of this AD) following
Viking Air Limited DHC–2 Beaver Service
Bulletin Number: V2/0005, Revision ‘NC’,
dated March 26, 2012; Viking Air Limited
DHC–2 Beaver Service Bulletin Number: V2/
0005, Revision ‘A’, dated November 7, 2014;
or Viking Air Limited DHC–2 Beaver Service
Bulletin Number: V2/0005, Revision ‘B’,
dated March 4, 2015.
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN: Aziz
Ahmed, Aerospace Engineer, FAA, New York
ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone: (516)
228–7329; fax: (516) 794–5531; email:
aziz.ahmed@faa.gov. Before using any
approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, 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
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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.
(p) Related Information
Refer to MCAI Transport Canada AD No.
CF–2015–21, dated July 30, 2015; and Viking
Air Limited DHC–2 Beaver Service Bulletin
Number: V2/0005, Revision ‘NC’, dated
March 26, 2012; Viking Air Limited DHC–2
Beaver Service Bulletin Number: V2/0005,
Revision ‘A’, dated November 7, 2014; or
Viking Air Limited DHC–2 Beaver Service
Bulletin Number: V2/0005, Revision ‘B’,
dated March 4, 2015, for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov/
document?D=FAA-2016-4229-0002.
(q) 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 the AD specifies otherwise.
(i) Viking DHC–2 Beaver Service Bulletin
Number: V2/0005, Revision ‘‘C’’, dated July
17, 2015.
(ii) Item 20A., of Part 3, in Appendix 2 of
Temporary Revision No.: 2–38, dated March
4, 2015, into the VIKING PSM NO.: 1–2–2,
AIRCRAFT: DHC–2 BEAVER, SERIES: ALL,
PUBLICATION: MAINTENANCE MANUAL.
(iii) Item 20A., in Part 4, of Temporary
Revision No.: 2T–14, dated March 4, 2015,
into VIKING PSM NO.: 1–2T–2, AIRCRAFT:
DHC–2 TURBO BEAVER, SERIES: ALL,
PUBLICATION: MAINTENANCE MANUAL.
(3) For Viking Air Limited service
information identified in this AD, contact
Viking Air Limited Technical Support, 1959
De Havilland Way, Sidney, British Columbia,
Canada, V8L 5V5; Fax: 250–656–0673;
telephone: (North America) (800) 663–8444;
email: technical.support@vikingair.com;
Internet: https://www.vikingair.com/support/
service-bulletins.
(4) You may view this service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148. In
addition, you can access this service
information on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2016–4229.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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64057
Issued in Kansas City, Missouri, on
September 8, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–22183 Filed 9–16–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5035; Directorate
Identifier 2015–NM–042–AD; Amendment
39–18650; AD 2016–19–01]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Fokker Services B.V. Model F28 Mark
0070 and Mark 0100 airplanes. This AD
was prompted by reports of cracking in
a certain area of the pressure bulkhead
webplate and skin connection angle.
This AD requires a one-time inspection
of the affected pressure bulkhead
webplate and skin connection angle,
and corrective actions if necessary. We
are issuing this AD to detect and correct
cracking of the pressure bulkhead
webplate and skin connection angle that
could lead to sudden inflight
decompression of the airplane, resulting
in injury to occupants.
DATES: This AD is effective October 24,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 24, 2016.
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 technicalservices@
fokker.com; Internet https://
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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5035.
SUMMARY:
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Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5035; 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 425–227–1139.
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 Mark 0100
airplanes. The NPRM published in the
Federal Register on March 29, 2016 (81
FR 17417) (‘‘the NPRM’’). The NPRM
was prompted by reports of cracking in
a certain area of the pressure bulkhead
webplate and skin connection angle.
The NPRM proposed to require a onetime inspection of the affected pressure
bulkhead webplate and skin connection
angle, and corrective actions if
necessary. We are issuing this AD to
detect and correct cracking of the
pressure bulkhead webplate and skin
connection angle that could lead to
sudden inflight decompression of the
airplane, resulting in injury to
occupants.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0024, dated February 19,
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
Mark 0100 airplanes. The MCAI states:
Service experience with the Fokker 100
type design has shown that cracking can
occur in the pressure bulkhead webplate and
skin connection angle on the right hand (RH)
side at station 14911 (station 12447 for F28
Mark 0070) at stringer 67 of fuselage section
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14:11 Sep 16, 2016
Jkt 238001
2, before reaching the existing threshold for
inspection per ALS [Airworthiness
Limitations Section] task 533016–00–03 (F28
Mark 0100) or task 533016–01–03 (F28 Mark
0070). Any cracks in this area are not visible
from the outside (covered by fairing) until
they reach a critical length.
This condition, if not detected and
corrected, could lead to sudden in-flight
decompression of the aeroplane, possibly
resulting in injury to occupants.
To address this potential unsafe condition,
Fokker Services published Service Bulletin
(SB) SBF100–53–128, which provides
inspection instructions to detect any crack in
the affected area.
For the reasons described above, this
[EASA] AD requires a one-time inspection of
the affected pressure bulkhead webplate and
skin connection angle, and, depending on
findings, accomplishment of applicable
corrective action(s).
This [EASA] AD is considered to be an
interim action and further AD action may
follow, possibly to lower the current ALS
task threshold, if justified by the inspection
results.
Corrective actions include repair of
cracking in the skin connection angle
and pressure bulkhead webplate, as
applicable.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5035.
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.
Related Service Information Under 1
CFR Part 51
We reviewed Fokker Service Bulletin
SBF100–53–128, dated November 12,
2014; and Fokker Service Bulletin
SBF100–53–129, dated February 16,
2015. The service information describes
procedures for inspection of the affected
pressure bulkhead webplate and skin
connection angle, and corrective actions
if necessary. This service information is
reasonably available because the
interested parties have access to it
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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 also estimate that it will take
about 1 work-hour per product to
comply with the basic requirements of
this AD, and 1 work-hour per product
for reporting. The average labor rate is
$85 per work-hour. Required parts will
cost about $0 per product. Based on
these figures, we estimate the cost of
this AD on U.S. operators to be $1,360,
or $170 per product.
In addition, we estimate that any
necessary follow-on actions will take
about 46 work-hours and require parts
costing $2,000, for a cost of $5,910 per
product. We have no way of
determining the number of aircraft that
might need these actions.
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
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Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–19–01 Fokker Services B.V.:
Amendment 39–18650. Docket No.
FAA–2016–5035; Directorate Identifier
2015–NM–042–AD.
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(a) Effective Date
This AD is effective October 24, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V.
Model F28 Mark 0070 and F28 Mark 0100
airplanes, certificated in any category, all
serial numbers.
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Jkt 238001
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of
cracking in the pressure bulkhead webplate
and skin connection angle. We are issuing
this AD to detect and correct cracking of the
pressure bulkhead webplate and skin
connection angle that could lead to sudden
inflight decompression of the airplane,
resulting in injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
At the time specified in paragraph (h) of
this AD: Do a detailed inspection of the
pressure bulkhead webplate and skin
connection angle on the right-hand side at
station 14911 (for Model F28 Mark 0100
airplanes) or station 12447 (for Model F28
Mark 0070 airplanes) at stringer 67 of
fuselage section 2, as applicable, in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–53–128, dated November 12, 2014.
This AD does not require action for airplanes
which, as of the effective date of this AD,
have accumulated less than 30,000 flight
cycles.
(1) If any crack is found in the skin
connection angle, before further flight, repair
the skin connection angle, in accordance
with the Accomplishment Instructions of
Fokker Service Bulletin SBF100–53–129,
dated February 16, 2015.
(2) If any crack is found in the pressure
bulkhead webplate, before further flight,
repair the pressure bulkhead webplate, in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–53–129, dated February 16, 2015.
(h) Compliance Times
At the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD, do the
actions required by paragraph (g) of this AD.
(1) For airplanes that have accumulated
less than 40,000 total flight cycles as of the
effective date of this AD, do the actions in
paragraph (g) of this AD within 2,000 flight
cycles after the effective date of this AD.
(2) For airplanes that have accumulated
40,000 or more total flight cycles as of the
effective date of this AD, do the actions in
paragraph (g) of this AD within 750 flight
cycles after the effective date of this AD.
(i) Reporting
Submit a report of the findings (both
positive and negative) of the inspection
required by paragraph (g) of this AD to
Fokker Services B.V. Engineering, Quality
Department P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone +31
(0)88–6280–350; fax +31 (0)88–6280–111;
email technicalservices@fokker.com; Internet
https://www.myfokkerfleet.com, in accordance
with the Accomplishment Instructions of
Fokker Service Bulletin SBF100–53–128,
dated November 12, 2014, at the applicable
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64059
time specified in paragraph (i)(1) or (i)(2) of
this AD. The report must include the
inspection results; the airplane serial
number; the total number of flight cycles and
flight hours on the airplane; a sketch or photo
to show the location of the crack(s) and
damaged part(s), if applicable; and the length
of each crack, if applicable.
(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.
(j) 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: 9-ANM-116AMOC-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.
(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 European Aviation Safety Agency
(EASA); or Fokker B.V. Service’s EASA
Design Organization Approval (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.
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Federal Register / Vol. 81, No. 181 / Monday, September 19, 2016 / Rules and Regulations
(k) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0024, dated
February 19, 2015, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2016–5035.
(l) 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–
128, dated November 12, 2014.
(ii) Fokker Service Bulletin SBF100–53–
129, dated February 16, 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 technicalservices@
fokker.com; Internet https://
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.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
September 6, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–22186 Filed 9–16–16; 8:45 am]
BILLING CODE 4910–13–P
SOCIAL SECURITY ADMINISTRATION
20 CFR Parts 404 and 416
[Docket No. SSA–2006–0149]
RIN 0960–AF58
Revised Medical Criteria for Evaluating
Respiratory System Disorders
Correction
In rule document 2016–13275,
appearing on pages 37138–37153, in the
issue of Thursday, June 9, 2016, make
the following correction:
PART 404—FEDERAL OLD AGE,
SURVIVORS AND DISABILITY
INSURANCE (1950) [CORRECTED]
On page 37147, in the Table titled
‘‘TABLE II—FVC CRITERIA FOR
3.02B’’, the column headings are
corrected to read as set forth below:
■
Table II–A
Height without shoes
(centimeters)
< means less than
Height without shoes
(inches)
< means less than
[FR Doc. C1–2016–13275 Filed 9–16–16; 8:45 am]
BILLING CODE 1505–01–D
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Parts 117 and 507
Current Good Manufacturing Practice,
Hazard Analysis, and Risk-Based
Preventive Controls for Human Food
and Current Good Manufacturing
Practice, Hazard Analysis, and RiskBased Preventive Controls for Food for
Animals; Definition of Qualified
Auditor; Announcement of Effective
Date
rmajette on DSK2TPTVN1PROD with RULES
Food and Drug Administration,
HHS.
Final rule; announcement of
effective date.
ACTION:
The Food and Drug
Administration (FDA or we) is
announcing the effective date for the
SUMMARY:
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14:11 Sep 16, 2016
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Age 18 to attainment of age 20
Age 20 or older
Females FVC
less than or
equal to
(L, BTPS)
definition of qualified auditor in the two
final rules that appeared in the Federal
Register of September 17, 2015.
DATES: The effective date of paragraph
(2) of the definition of qualified auditor
in 21 CFR 117.3 and in 21 CFR 507.3,
which published in the Federal Register
of September 17, 2015 (80 FR 55908)
and (80 FR 56170), is September 19,
2016.
For
questions relating to Current Good
Manufacturing Practice, Hazard
Analysis and Risk-Based Preventive
Controls for Human Food: Jenny Scott,
Center for Food Safety and Applied
Nutrition (HFS–300), Food and Drug
Administration, 5001 Campus Dr.,
College Park, MD 20740, 240–402–2166.
For questions relating to Current Good
Manufacturing Practice, Hazard
Analysis, and Risk-Based Preventive
Controls for Food for Animals: Jeanette
Murphy, Center for Veterinary Medicine
(HFV–200), Food and Drug
Administration, 7519 Standish Pl.,
Rockville, MD 20855, 240–402–6246.
SUPPLEMENTARY INFORMATION: In the
Federal Register of September 17, 2015
(80 FR 55908), we published a final rule
FOR FURTHER INFORMATION CONTACT:
[Docket Nos. FDA–2011–N–0920, FDA–
2011–N–0922]
AGENCY:
Table II–B
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
Males FVC
less than or
equal to
(L, BTPS)
Females FVC
less than or
equal to
(L, BTPS)
Males FVC
less than or
equal to
(L, BTPS)
for ‘‘Current Good Manufacturing
Practices, Hazard Analysis, and RiskBased Preventive Controls for Human
Food’’ (preventive controls for human
food rule). In § 117.3, we included the
definition of a qualified auditor. In the
definition, we provided examples of
qualified auditors. Paragraph 2 of the
definition reads ‘‘An audit agent of a
certification body that is accredited in
accordance with regulations in part 1,
subpart M of this chapter.’’ At the time
the final rule published, paragraph 2
referred to a provision in a future final
rule: ‘‘Accreditation of Third-Party
Certification Bodies to Conduct Food
Safety Audits to Issue Certifications’’
(third-party certification rule). In the
preamble to the preventive controls for
human food rule, we stated that we
would publish a document in the
Federal Register announcing the
effective date of paragraph (2) once we
finalized the third-party certification
rule (80 FR 55908 at 55954).
In the Federal Register of September
17, 2015 (80 FR 56170), we published a
final rule for ‘‘Current Good
Manufacturing Practices, Hazard
Analysis, and Risk-Based Preventive
Controls for Food for Animals’’
E:\FR\FM\19SER1.SGM
19SER1
]]>Agencies
[Federal Register Volume 81, Number 181 (Monday, September 19, 2016)]
[Rules and Regulations]
[Pages 64057-64060]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-22186]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5035; Directorate Identifier 2015-NM-042-AD;
Amendment 39-18650; AD 2016-19-01]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Fokker Services B.V. Model F28 Mark 0070 and Mark 0100 airplanes. This
AD was prompted by reports of cracking in a certain area of the
pressure bulkhead webplate and skin connection angle. This AD requires
a one-time inspection of the affected pressure bulkhead webplate and
skin connection angle, and corrective actions if necessary. We are
issuing this AD to detect and correct cracking of the pressure bulkhead
webplate and skin connection angle that could lead to sudden inflight
decompression of the airplane, resulting in injury to occupants.
DATES: This AD is effective October 24, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 24,
2016.
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 technicalservices@fokker.com; Internet https://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 https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-5035.
[[Page 64058]]
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5035; 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 425-227-1139.
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 Mark 0100 airplanes. The NPRM published in the
Federal Register on March 29, 2016 (81 FR 17417) (``the NPRM''). The
NPRM was prompted by reports of cracking in a certain area of the
pressure bulkhead webplate and skin connection angle. The NPRM proposed
to require a one-time inspection of the affected pressure bulkhead
webplate and skin connection angle, and corrective actions if
necessary. We are issuing this AD to detect and correct cracking of the
pressure bulkhead webplate and skin connection angle that could lead to
sudden inflight decompression of the airplane, resulting in injury to
occupants.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0024, dated February 19, 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 Mark 0100 airplanes. The MCAI states:
Service experience with the Fokker 100 type design has shown
that cracking can occur in the pressure bulkhead webplate and skin
connection angle on the right hand (RH) side at station 14911
(station 12447 for F28 Mark 0070) at stringer 67 of fuselage section
2, before reaching the existing threshold for inspection per ALS
[Airworthiness Limitations Section] task 533016-00-03 (F28 Mark
0100) or task 533016-01-03 (F28 Mark 0070). Any cracks in this area
are not visible from the outside (covered by fairing) until they
reach a critical length.
This condition, if not detected and corrected, could lead to
sudden in-flight decompression of the aeroplane, possibly resulting
in injury to occupants.
To address this potential unsafe condition, Fokker Services
published Service Bulletin (SB) SBF100-53-128, which provides
inspection instructions to detect any crack in the affected area.
For the reasons described above, this [EASA] AD requires a one-
time inspection of the affected pressure bulkhead webplate and skin
connection angle, and, depending on findings, accomplishment of
applicable corrective action(s).
This [EASA] AD is considered to be an interim action and further
AD action may follow, possibly to lower the current ALS task
threshold, if justified by the inspection results.
Corrective actions include repair of cracking in the skin connection
angle and pressure bulkhead webplate, as applicable.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5035.
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.
Related Service Information Under 1 CFR Part 51
We reviewed Fokker Service Bulletin SBF100-53-128, dated November
12, 2014; and Fokker Service Bulletin SBF100-53-129, dated February 16,
2015. The service information describes procedures for inspection of
the affected pressure bulkhead webplate and skin connection angle, and
corrective actions if necessary. 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 also estimate that it will take about 1 work-hour per product to
comply with the basic requirements of this AD, and 1 work-hour per
product for reporting. The average labor rate is $85 per work-hour.
Required parts will cost about $0 per product. Based on these figures,
we estimate the cost of this AD on U.S. operators to be $1,360, or $170
per product.
In addition, we estimate that any necessary follow-on actions will
take about 46 work-hours and require parts costing $2,000, for a cost
of $5,910 per product. We have no way of determining the number of
aircraft that might need these actions.
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
[[Page 64059]]
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):
2016-19-01 Fokker Services B.V.: Amendment 39-18650. Docket No. FAA-
2016-5035; Directorate Identifier 2015-NM-042-AD.
(a) Effective Date
This AD is effective October 24, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Fokker Services B.V. Model F28 Mark 0070 and
F28 Mark 0100 airplanes, certificated in any category, all serial
numbers.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracking in the pressure
bulkhead webplate and skin connection angle. We are issuing this AD
to detect and correct cracking of the pressure bulkhead webplate and
skin connection angle that could lead to sudden inflight
decompression of the airplane, resulting in injury to occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
At the time specified in paragraph (h) of this AD: Do a detailed
inspection of the pressure bulkhead webplate and skin connection
angle on the right-hand side at station 14911 (for Model F28 Mark
0100 airplanes) or station 12447 (for Model F28 Mark 0070 airplanes)
at stringer 67 of fuselage section 2, as applicable, in accordance
with the Accomplishment Instructions of Fokker Service Bulletin
SBF100-53-128, dated November 12, 2014. This AD does not require
action for airplanes which, as of the effective date of this AD,
have accumulated less than 30,000 flight cycles.
(1) If any crack is found in the skin connection angle, before
further flight, repair the skin connection angle, in accordance with
the Accomplishment Instructions of Fokker Service Bulletin SBF100-
53-129, dated February 16, 2015.
(2) If any crack is found in the pressure bulkhead webplate,
before further flight, repair the pressure bulkhead webplate, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF100-53-129, dated February 16, 2015.
(h) Compliance Times
At the applicable time specified in paragraph (h)(1) or (h)(2)
of this AD, do the actions required by paragraph (g) of this AD.
(1) For airplanes that have accumulated less than 40,000 total
flight cycles as of the effective date of this AD, do the actions in
paragraph (g) of this AD within 2,000 flight cycles after the
effective date of this AD.
(2) For airplanes that have accumulated 40,000 or more total
flight cycles as of the effective date of this AD, do the actions in
paragraph (g) of this AD within 750 flight cycles after the
effective date of this AD.
(i) Reporting
Submit a report of the findings (both positive and negative) of
the inspection required by paragraph (g) of this AD to Fokker
Services B.V. Engineering, Quality Department P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31
(0)88-6280-111; email technicalservices@fokker.com; Internet https://www.myfokkerfleet.com, in accordance with the Accomplishment
Instructions of Fokker Service Bulletin SBF100-53-128, dated
November 12, 2014, at the applicable time specified in paragraph
(i)(1) or (i)(2) of this AD. The report must include the inspection
results; the airplane serial number; the total number of flight
cycles and flight hours on the airplane; a sketch or photo to show
the location of the crack(s) and damaged part(s), if applicable; and
the length of each crack, if applicable.
(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.
(j) 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: 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.
(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
European Aviation Safety Agency (EASA); or Fokker B.V. Service's
EASA Design Organization Approval (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.
[[Page 64060]]
(k) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2015-0024, dated February 19, 2015, for
related information. This MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2016-5035.
(l) 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 SBF100-53-128, dated November 12,
2014.
(ii) Fokker Service Bulletin SBF100-53-129, dated February 16,
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 technicalservices@fokker.com; Internet https://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.
(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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on September 6, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-22186 Filed 9-16-16; 8:45 am]
BILLING CODE 4910-13-P
