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)

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


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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).

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

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.

(c) Applicability

    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 [email protected]; 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: [email protected]. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. 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 [email protected]; 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