81 FR 17417 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 60 (March 29, 2016)

Page Range		17417-17420
FR Document		2016-07022

We propose to adopt a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and Mark 0100 airplanes. This proposed AD was prompted by reports of cracking in a certain area of the pressure bulkhead webplate and skin connection angle. This proposed AD would require a one-time inspection of the affected pressure bulkhead webplate and skin connection angle, and corrective actions if necessary. We are proposing 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.

Federal Register, Volume 81 Issue 60 (Tuesday, March 29, 2016)

[Federal Register Volume 81, Number 60 (Tuesday, March 29, 2016)]
[Proposed Rules]
[Pages 17417-17420]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2016-07022]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5035; Directorate Identifier 2015-NM-042-AD]
RIN 2120-AA64

Airworthiness Directives; Fokker Services B.V. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Fokker Services B.V. Model F.28 Mark 0070 and Mark 0100 airplanes. This
proposed AD was prompted by reports of cracking in a certain area of
the pressure bulkhead webplate and skin connection angle. This proposed
AD would require a one-time inspection of the affected pressure
bulkhead webplate and skin connection angle, and corrective actions if
necessary. We are proposing 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: We must receive comments on this proposed AD by May 13, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.

[[Page 17418]]

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.
For service information identified in this proposed 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 http://www.myfokkerfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1137;
fax 425-227-1139.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5035;
Directorate Identifier 2015-NM-042-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0024, 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 F.28 Mark 0070 and Mark 0100 series 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 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5035.

Related Service Information Under 1 CFR Part 51

Fokker Services B.V. has issued 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.

FAA's Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.

Differences Between This Proposed AD and the MCAI and Service
Information

Although the MCAI and service information allow further flight
after cracks are found during compliance with the proposed actions,
paragraph (g)(2) of this proposed AD requires that you repair the crack
before further flight.

Costs of Compliance

We estimate that this proposed AD affects 8 airplanes of U.S.
registry.
We also estimate that it would take about 1 work-hour per product
to comply with the basic requirements of this proposed AD, and 1 work-
hour per product for reporting. The average labor rate is $85 per work-
hour. Required parts would cost about $0 per product. Based on these
figures, we estimate the cost of this proposed AD on U.S. operators to
be $1,360, or $170 per product.
In addition, we estimate that any necessary follow-on actions would
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

[[Page 17419]]

OMB control number. The control number for the collection of
information required by this proposed AD is 2120-0056. The paperwork
cost associated with this proposed AD has been detailed in the Costs of
Compliance section of this document and includes time for reviewing
instructions, as well as completing and reviewing the collection of
information. Therefore, all reporting associated with this proposed AD
is mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA at
800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):

Fokker Services B.V.: Docket No. FAA-2016-5035; Directorate
Identifier 2015-NM-042-AD.

(a) Comments Due Date

We must receive comments by May 13, 2016.

(b) Affected ADs

None.

This AD applies to Fokker Services B.V. Model F.28 Mark 0070 and
F.28 Mark 0100 airplanes, all serial numbers, certificated in any
category.

(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 on the right-hand (RH)
side at station 14911 (for Model F.28 Mark 0100 airplanes) or
station 12447 (for Model F.28 Mark 0070 airplanes) at stringer 67 of
fuselage section 2. 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 RH 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 (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) 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) 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 http://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

[[Page 17420]]

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. The AMOC approval letter must
specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
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.

(k) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (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 http://www.regulations.gov by searching for and locating Docket
No. FAA-2016-5035.
(2) For service information identified in this AD, contact
Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130
EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31
(0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com. You may view this service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call 425-227-1221.

Issued in Renton, Washington, on March 20, 2016.
Michael Kaszycki,
Acting Manager Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-07022 Filed 3-28-16; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17417

For the reasons discussed above, I (g) Repetitive Inspections Renton, WA 98057–3356; phone: 425–917–
certify this proposed regulation: At the applicable compliance time 6595; fax: 425–917–6590; email:
(1) Is not a ‘‘significant regulatory specified in paragraph 1.E., ‘‘Compliance,’’ of Jason.deutschman@faa.gov.
action’’ under Executive Order 12866, Boeing Alert Service Bulletin 737–53A1352, (2) For service information identified in
(2) Is not a ‘‘significant rule’’ under dated October 2, 2015, do a low frequency this AD, contact Boeing Commercial
eddy current inspection for cracking of the Airplanes, Attention: Data & Services
the DOT Regulatory Policies and
lower fastener row of S–14L and S–14R lap Management, P.O. Box 3707, MC 2H–65,
Procedures (44 FR 11034, February 26, Seattle, WA 98124–2207; telephone 206–
1979), splices, in accordance with the
Accomplishment Instructions of Boeing Alert 544–5000, extension 1; fax 206–766–5680;
(3) Will not affect intrastate aviation Internet https://www.myboeingfleet.com. You
Service Bulletin 737–53A1352, dated October
in Alaska, and 2, 2015. Repeat the inspection thereafter at may view this referenced service information
(4) Will not have a significant the applicable times specified in paragraph at the FAA, Transport Airplane Directorate,
economic impact, positive or negative, 1.E., ‘‘Compliance,’’ of Boeing Alert Service 1601 Lind Avenue SW., Renton, WA. For
on a substantial number of small entities Bulletin 737–53A1352, dated October 2, information on the availability of this
under the criteria of the Regulatory 2015. If any cracking is found, before further material at the FAA, call 425–227–1221.
Flexibility Act. flight, repair using a method approved in Issued in Renton Washington, on March
accordance with the procedures specified in 20, 2016.
List of Subjects in 14 CFR Part 39 paragraph (h) of this AD.
Michael Kaszycki,
Air transportation, Aircraft, Aviation (h) Alternative Methods of Compliance Acting Manager, Transport Airplane
safety, Incorporation by reference, (AMOCs) Directorate, Aircraft Certification Service.
Safety. (1) The Manager, Seattle Aircraft [FR Doc. 2016–07023 Filed 3–28–16; 8:45 am]
The Proposed Amendment Certification Office (ACO), FAA, has the BILLING CODE 4910–13–P
authority to approve AMOCs for this AD, if
Accordingly, under the authority requested using the procedures found in 14
delegated to me by the Administrator, CFR 39.19. In accordance with 14 CFR 39.19,
the FAA proposes to amend 14 CFR part send your request to your principal inspector
DEPARTMENT OF TRANSPORTATION
39 as follows: or local Flight Standards District Office, as
appropriate. If sending information directly Federal Aviation Administration
PART 39—AIRWORTHINESS to the manager of the ACO, send it to the
DIRECTIVES attention of the person identified in 14 CFR Part 39
paragraph (i)(1) of this AD. Information may
[Docket No. FAA–2016–5035; Directorate
■ 1. The authority citation for part 39 be emailed to: 9-ANM-Seattle-ACO-AMOC-
Identifier 2015–NM–042–AD]
continues to read as follows: Requests@faa.gov.
(2) Before using any approved AMOC, RIN 2120–AA64
Authority: 49 U.S.C. 106(g), 40113, 44701. notify your appropriate principal inspector,
§ 39.13 [Amended] or lacking a principal inspector, the manager Airworthiness Directives; Fokker
of the local flight standards district office/ Services B.V. Airplanes
■ 2. The FAA amends § 39.13 by adding certificate holding district office.
the following new airworthiness (3) An AMOC that provides an acceptable AGENCY: Federal Aviation
directive (AD): level of safety may be used for any repair, Administration (FAA), DOT.
The Boeing Company: Docket No. FAA– modification, or alteration required by this ACTION: Notice of proposed rulemaking
2016–5034; Directorate Identifier 2015– AD if it is approved by the Boeing
Commercial Airplanes Organization
(NPRM).
NM–172–AD.
Designation Authorization (ODA) that has
(a) Comments Due Date SUMMARY: We propose to adopt a new
been authorized by the Manager, Seattle
We must receive comments by May 13, ACO, to make those findings. To be airworthiness directive (AD) for all
2016. approved, the repair method, modification Fokker Services B.V. Model F.28 Mark
deviation, or alteration deviation must meet 0070 and Mark 0100 airplanes. This
(b) Affected ADs proposed AD was prompted by reports
the certification basis of the airplane, and the
None. approval must specifically refer to this AD. of cracking in a certain area of the
(c) Applicability (4) For service information that contains pressure bulkhead webplate and skin
steps that are labeled as Required for connection angle. This proposed AD
This AD applies to all The Boeing Compliance (RC), the provisions of
Company Model 737–600, –700, –700C, would require a one-time inspection of
paragraphs (h)(4)(i) and (h)(4)(ii) of this AD
–800, –900, and –900ER series airplanes, the affected pressure bulkhead webplate
apply.
certificated in any category. (i) The steps labeled as RC, including and skin connection angle, and
(d) Subject substeps under an RC step and any figures corrective actions if necessary. We are
identified in an RC step, must be done to proposing this AD to detect and correct
Air Transport Association (ATA) of cracking of the pressure bulkhead
America Code 53, Fuselage. comply with the AD. An AMOC is required
for any deviations to RC steps, including webplate and skin connection angle that
(e) Unsafe Condition substeps and identified figures. could lead to sudden inflight
This AD was prompted by an evaluation by (ii) Steps not labeled as RC may be decompression of the airplane resulting
the design approval holder (DAH) indicating deviated from using accepted methods in in injury to occupants.
that the S–14L and S–14R lap splices are accordance with the operator’s maintenance
or inspection program without obtaining DATES: We must receive comments on
subject to widespread fatigue damage (WFD).
approval of an AMOC, provided the RC steps, this proposed AD by May 13, 2016.
mstockstill on DSK4VPTVN1PROD with PROPOSALS

We are issuing this AD to detect and correct
widespread cracking in the S–14L and S–14R including substeps and identified figures, can ADDRESSES: You may send comments,
lap splices that could rapidly link up and still be done as specified, and the airplane using the procedures found in 14 CFR
result in possible rapid decompression and can be put back in an airworthy condition. 11.43 and 11.45, by any of the following
reduced structural integrity of the airplane. methods:
(i) Related Information
(f) Compliance (1) For more information about this AD, • Federal eRulemaking Portal: Go to
Comply with this AD within the contact Jason Deutschman, Aerospace http://www.regulations.gov. Follow the
compliance times specified, unless already Engineer, Airframe Branch, ANM–120S, instructions for submitting comments.
done. FAA, Seattle ACO, 1601 Lind Avenue SW., • Fax: 202–493–2251.

VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1

17418 Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules

• Mail: U.S. Department of We will post all comments we service information describes
Transportation, Docket Operations, M– receive, without change, to http:// procedures for inspection of the affected
30, West Building Ground Floor, Room www.regulations.gov, including any pressure bulkhead webplate and skin
W12–140, 1200 New Jersey Avenue SE., personal information you provide. We connection angle, and corrective actions
Washington, DC 20590. will also post a report summarizing each if necessary. This service information is
• Hand Delivery: U.S. Department of substantive verbal contact we receive reasonably available because the
Transportation, Docket Operations, M– about this proposed AD. interested parties have access to it
30, West Building Ground Floor, Room through their normal course of business
Discussion
W12–140, 1200 New Jersey Avenue SE., or by the means identified in the
Washington, DC, between 9 a.m. and 5 The European Aviation Safety Agency ADDRESSES section.
p.m., Monday through Friday, except (EASA), which is the Technical Agent
for the Member States of the European FAA’s Determination and Requirements
Federal holidays.
Union, has issued EASA Airworthiness of This Proposed AD
For service information identified in
this proposed AD, contact Fokker Directive 2015–0024, dated February 19, This product has been approved by
Services B.V., Technical Services Dept., 2015 (referred to after this as the the aviation authority of another
P.O. Box 1357, 2130 EL Hoofddorp, the Mandatory Continuing Airworthiness country, and is approved for operation
Netherlands; telephone +31 (0)88–6280– Information, or ‘‘the MCAI’’), to correct in the United States. Pursuant to our
350; fax +31 (0)88–6280–111; email an unsafe condition for all Fokker bilateral agreement with the State of
technicalservices@fokker.com; Internet Services B.V. Model F.28 Mark 0070 Design Authority, we have been notified
http://www.myfokkerfleet.com. You may and Mark 0100 series airplanes. The of the unsafe condition described in the
view this referenced service information MCAI states: MCAI and service information
at the FAA, Transport Airplane Service experience with the Fokker 100 referenced above. We are proposing this
Directorate, 1601 Lind Avenue SW., type design has shown that cracking can AD because we evaluated all pertinent
Renton, WA. For information on the occur in the pressure bulkhead webplate and information and determined an unsafe
availability of this material at the FAA, skin connection angle on the right hand (RH) condition exists and is likely to exist or
call 425–227–1221. side at station 14911 (station 12447 for F28 develop on other products of the same
Mark 0070) at stringer 67 of fuselage section type design.
Examining the AD Docket 2, before reaching the existing threshold for
inspection per ALS [Airworthiness Differences Between This Proposed AD
You may examine the AD docket on Limitations Section] task 533016–00–03 (F28 and the MCAI and Service Information
the Internet at http:// Mark 0100) or task 533016–01–03 (F28 Mark
www.regulations.gov by searching for 0070). Any cracks in this area are not visible Although the MCAI and service
and locating Docket No. FAA–2016– from the outside (covered by fairing) until information allow further flight after
5035; or in person at the Docket they reach a critical length. cracks are found during compliance
Management Facility between 9 a.m. This condition, if not detected and with the proposed actions, paragraph
and 5 p.m., Monday through Friday, corrected, could lead to sudden in-flight (g)(2) of this proposed AD requires that
decompression of the aeroplane, possibly you repair the crack before further
except Federal holidays. The AD docket resulting in injury to occupants.
contains this proposed AD, the flight.
To address this potential unsafe condition,
regulatory evaluation, any comments Fokker Services published Service Bulletin Costs of Compliance
received, and other information. The (SB) SBF100–53–128, which provides
street address for the Docket Operations inspection instructions to detect any crack in
We estimate that this proposed AD
office (telephone 800–647–5527) is in the affected area. affects 8 airplanes of U.S. registry.
For the reasons described above, this We also estimate that it would take
the ADDRESSES section. Comments will
[EASA] AD requires a one-time inspection of about 1 work-hour per product to
be available in the AD docket shortly
the affected pressure bulkhead webplate and comply with the basic requirements of
after receipt.
skin connection angle, and, depending on this proposed AD, and 1 work-hour per
FOR FURTHER INFORMATION CONTACT: Tom findings, accomplishment of applicable product for reporting. The average labor
Rodriguez, Aerospace Engineer, corrective action(s). rate is $85 per work-hour. Required
International Branch, ANM–116, This AD is considered to be an interim parts would cost about $0 per product.
Transport Airplane Directorate, FAA, action and further AD action may follow, Based on these figures, we estimate the
1601 Lind Avenue SW., Renton, WA possibly to lower the current ALS task
threshold, if justified by the inspection
cost of this proposed AD on U.S.
98057–3356; telephone 425–227–1137; operators to be $1,360, or $170 per
fax 425–227–1139. results.
product.
SUPPLEMENTARY INFORMATION: Corrective actions include repair of In addition, we estimate that any
Comments Invited cracking in the skin connection angle necessary follow-on actions would take
and pressure bulkhead webplate, as about 46 work-hours and require parts
We invite you to send any written applicable. costing $2,000, for a cost of $5,910 per
relevant data, views, or arguments about You may examine the MCAI in the product. We have no way of
this proposed AD. Send your comments AD docket on the Internet at http:// determining the number of aircraft that
to an address listed under the www.regulations.gov by searching for might need these actions.
ADDRESSES section. Include ‘‘Docket No. and locating Docket No. FAA–2016–
FAA–2016–5035; Directorate Identifier Paperwork Reduction Act
mstockstill on DSK4VPTVN1PROD with PROPOSALS

5035.
2015–NM–042–AD’’ at the beginning of A federal agency may not conduct or
your comments. We specifically invite Related Service Information Under 1 sponsor, and a person is not required to
comments on the overall regulatory, CFR Part 51 respond to, nor shall a person be subject
economic, environmental, and energy Fokker Services B.V. has issued to penalty for failure to comply with a
aspects of this proposed AD. We will Fokker Service Bulletin SBF100–53– collection of information subject to the
consider all comments received by the 128, dated November 12, 2014; and requirements of the Paperwork
closing date and may amend this Fokker Service Bulletin SBF100–53– Reduction Act unless that collection of
proposed AD based on those comments. 129, dated February 16, 2015. The information displays a current valid

VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1

Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17419

OMB control number. The control List of Subjects in 14 CFR Part 39 action for airplanes which, as of the effective
number for the collection of information date of this AD, have accumulated less than
Air transportation, Aircraft, Aviation 30,000 flight cycles.
required by this proposed AD is 2120– safety, Incorporation by reference, (1) If any crack is found in the skin
0056. The paperwork cost associated Safety. connection angle, before further flight, repair
with this proposed AD has been the skin connection angle, in accordance
detailed in the Costs of Compliance The Proposed Amendment with the Accomplishment Instructions of
section of this document and includes Accordingly, under the authority Fokker Service Bulletin SBF100–53–129,
time for reviewing instructions, as well delegated to me by the Administrator, dated February 16, 2015.
as completing and reviewing the the FAA proposes to amend 14 CFR part (2) If any crack is found in the pressure
collection of information. Therefore, all bulkhead webplate, before further flight,
39 as follows:
reporting associated with this proposed repair the pressure bulkhead webplate, in
accordance with the Accomplishment
AD is mandatory. Comments concerning PART 39—AIRWORTHINESS
Instructions of Fokker Service Bulletin
the accuracy of this burden and DIRECTIVES SBF100–53–129, dated February 16, 2015.
suggestions for reducing the burden
should be directed to the FAA at 800 ■ 1. The authority citation for part 39 (h) Compliance Times
Independence Ave. SW., Washington, continues to read as follows: At the applicable time specified in (h)(1) or
DC 20591, ATTN: Information Authority: 49 U.S.C. 106(g), 40113, 44701. (h)(2) of this AD, do the actions required by
Collection Clearance Officer, AES–200. paragraph (g) of this AD.
§ 39.13 [Amended] (1) For airplanes that have accumulated
Authority for This Rulemaking ■ 2. The FAA amends § 39.13 by adding less than 40,000 total flight cycles as of the
the following new airworthiness effective date of this AD, do the actions in
Title 49 of the United States Code paragraph (g) within 2,000 flight cycles after
specifies the FAA’s authority to issue directive (AD): the effective date of this AD.
rules on aviation safety. Subtitle I, Fokker Services B.V.: Docket No. FAA– (2) For airplanes that have accumulated
section 106, describes the authority of 2016–5035; Directorate Identifier 2015– 40,000 or more total flight cycles as of the
the FAA Administrator. ‘‘Subtitle VII: NM–042–AD. effective date of this AD, do the actions in
Aviation Programs,’’ describes in more paragraph (g) within 750 flight cycles after
(a) Comments Due Date the effective date of this AD.
detail the scope of the Agency’s
We must receive comments by May 13,
authority. (i) Reporting
2016.
We are issuing this rulemaking under Submit a report of the findings (both
the authority described in ‘‘Subtitle VII, (b) Affected ADs positive and negative) of the inspection
Part A, Subpart III, Section 44701: None. required by paragraph (g) of this AD to
General requirements.’’ Under that Fokker Services B.V. Engineering, Quality
(c) Applicability
section, Congress charges the FAA with Department P.O. Box 1357, 2130 EL
promoting safe flight of civil aircraft in This AD applies to Fokker Services B.V. Hoofddorp, the Netherlands; telephone +31
air commerce by prescribing regulations Model F.28 Mark 0070 and F.28 Mark 0100 (0)88–6280–350; fax +31 (0)88–6280–111;
airplanes, all serial numbers, certificated in email technicalservices@fokker.com; Internet
for practices, methods, and procedures
any category. http://www.myfokkerfleet.com in accordance
the Administrator finds necessary for with the Accomplishment Instructions of
safety in air commerce. This regulation (d) Subject
Fokker Service Bulletin SBF100–53–128,
is within the scope of that authority Air Transport Association (ATA) of dated November 12, 2014, at the applicable
because it addresses an unsafe condition America Code 53, Fuselage. time specified in paragraph (i)(1) or (i)(2) of
that is likely to exist or develop on (e) Reason
this AD. The report must include the
products identified in this rulemaking inspection results; the airplane serial
This AD was prompted by reports of number; the total number of flight cycles and
action.
cracking in the pressure bulkhead webplate flight hours on the airplane; a sketch or photo
Regulatory Findings and skin connection angle on the right-hand to show the location of the crack(s) and
(RH) side at station 14911 (for Model F.28 damaged part(s), if applicable; and the length
We determined that this proposed AD Mark 0100 airplanes) or station 12447 (for of each crack, if applicable.
would not have federalism implications Model F.28 Mark 0070 airplanes) at stringer (1) If the inspection was done on or after
under Executive Order 13132. This 67 of fuselage section 2. We are issuing this the effective date of this AD: Submit the
proposed AD would not have a AD to detect and correct cracking of the report within 30 days after the inspection.
substantial direct effect on the States, on pressure bulkhead webplate and skin (2) If the inspection was done before the
the relationship between the national connection angle that could lead to sudden effective date of this AD: Submit the report
Government and the States, or on the inflight decompression of the airplane within 30 days after the effective date of this
distribution of power and resulting in injury to occupants. AD.
responsibilities among the various (f) Compliance (j) Other FAA AD Provisions
levels of government. Comply with this AD within the The following provisions also apply to this
For the reasons discussed above, I compliance times specified, unless already AD:
certify this proposed regulation: done. (1) Alternative Methods of Compliance
1. Is not a ‘‘significant regulatory (AMOCs): The Manager, International
(g) Inspection
action’’ under Executive Order 12866; Branch, ANM–116, Transport Airplane
2. Is not a ‘‘significant rule’’ under the At the time specified in paragraph (h) of Directorate, FAA, has the authority to
this AD: Do a detailed inspection of the approve AMOCs for this AD, if requested
mstockstill on DSK4VPTVN1PROD with PROPOSALS

DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); pressure bulkhead webplate and skin using the procedures found in 14 CFR 39.19.
3. Will not affect intrastate aviation in connection angle on the RH side at station In accordance with 14 CFR 39.19, send your
14911 (for Model F28 Mark 0100 airplanes) request to your principal inspector or local
Alaska; and or station 12447 (for Model F28 Mark 0070 Flight Standards District Office, as
4. Will not have a significant airplanes) at stringer 67 of fuselage section 2, appropriate. If sending information directly
economic impact, positive or negative, as applicable, in accordance with the to the International Branch, send it to ATTN:
on a substantial number of small entities Accomplishment Instructions of Fokker Tom Rodriguez, Aerospace Engineer,
under the criteria of the Regulatory Service Bulletin SBF100–53–128, dated International Branch, ANM–116, Transport
Flexibility Act. November 12, 2014. This AD does not require Airplane Directorate, FAA, 1601 Lind

VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1

Document Created: 2016-03-30 08:29:31
Document Modified: 2016-03-30 08:29:31

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		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by May 13, 2016.
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.
FR Citation		81 FR 17417
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

81 FR 17417 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 60 (March 29, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration