81 FR 64057 - Airworthiness Directives; Fokker Services B.V. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 181 (September 19, 2016)

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.

[Federal Register Volume 81, Number 181 (Monday, September 19, 2016)]
[Rules and Regulations]
[Pages 64057-64060]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-22186]


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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; 
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.

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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 [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. It is also available on the 
Internet at http://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 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 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 http://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 [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 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.
    (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 http://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 [email protected]; Internet http://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: http://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