81 FR 87419 - Airworthiness Directives; Fokker Services B.V. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 233 (December 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 233 (December 5, 2016)
| Page Range | 87419-87422 | |
| FR Document | 2016-28601 |
[Federal Register Volume 81, Number 233 (Monday, December 5, 2016)] [Rules and Regulations] [Pages 87419-87422] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-28601] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-7271; Directorate Identifier 2015-NM-099-AD; Amendment 39-18722; AD 2016-24-05] 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 0100 airplanes. This AD was prompted by heavy corrosion found on the wing rear spar lower girder. This AD requires inspections of the affected areas, modification of the wing trailing edge lower skin panels, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 9, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 9, 2017. 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-2016-7271. 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- 7271; 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 425-227-1149. 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 0100 airplanes. The NPRM published in the Federal Register on June 23, 2016 (81 FR 40823) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0113, dated June 22, 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 0100 airplanes. The MCAI states: On an F28 Mark 0070 aeroplane, heavy corrosion was found on the wing rear spar lower girder. At small spots the effective thickness of the vertical flange of the lower girder was almost lost. Subsequently, a number of inspections were accomplished on other aeroplanes to provide additional information on possible corrosion in this area. Because the rear spar lower girder between Wing Stations (WSTA) 9270 and 11794 is hidden from view by the inboard and outboard aileron balancing plates, it is possible that corrosion in this area remains undetected during the zonal inspections in zone 536 and 636 (MRB [Maintenance Review Board] tasks 062505-00-01 and 062605-00-01).The heavy corrosion was not only found in the area between WSTA 9270 and 11794, but also in the area where the rear spar lower girder is directly visible. This condition, if not detected and corrected, reduces the load carrying capability of the wing, possibly resulting in structural failure and loss of the aeroplane. To address this potential unsafe condition, Fokker Services issued Service Bulletin (SB) SBF100-57-049 to provide instructions to detect and remove corrosion and to modify the wing trailing edge lower skin panels into access panels. SBF100-57-050 was issued to provide repair instructions. For the reasons described above, this [EASA] AD requires inspections of the affected areas and, depending on findings, accomplishment of applicable corrective action(s) [including removing corrosion, repair, and restoring protective finish]. This [EASA] AD also requires modification of the wing trailing edge lower skin panels into access panels [This modification is to provide ease of access for later inspection and repairs in the affected areas.], and reporting of the results of the inspections to Fokker Services. More information on this subject can be found in Fokker Services All Operators Message AOF100.197. 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- 7271. 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. [[Page 87420]] Related Service Information Under 1 CFR Part 51 We reviewed Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, which describes procedures for an inspection for corrosion of certain wing rear spar lower girder areas, modification of the wing trailing edge lower skin panels, and corrective actions if necessary. We also reviewed Fokker Service Bulletin SBF100-57-050, Revision 1, dated May 19, 2015, which describes procedures for repair of the wing spar. 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 estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Wing inspection and 35 work-hours x $85 per $1,680 $4,655 per $37,240 per modification. hour = $2,975 per inspection cycle. inspection cycle. inspection cycle. Reporting...................... 1 work hour x $85 per 0 85................ 680. hour = $85. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary corrective actions that will be required based on the results of the required inspection. We have no way of determining the number of airplanes that might need these corrective actions: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Corrective Actions............... Up to 372 work hours x Up to $7,600........ Up to $39,220. $85 per hour = $31,620. ---------------------------------------------------------------------------------------------------------------- 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 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): 2016-24-05 Fokker Services B.V.: Amendment 39-18722; Docket No. FAA- 2016-7271; Directorate Identifier 2015-NM-099-AD. (a) Effective Date This AD is effective January 9, 2017. (b) Affected ADs None. (c) Applicability This AD applies to all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. [[Page 87421]] (e) Reason This AD was prompted by heavy corrosion found on the wing rear spar lower girder. We are issuing this AD to detect and correct corrosion of the wing rear spar lower girder. This condition could reduce the load-carrying capability of the wing, possibly resulting in structural failure and loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the Wing Rear Spar Lower Girder From Wing Stations (WSTA) 9270 to 11794 Within 1,000 flight cycles or 12 months, whichever occurs first after the effective date of this AD, accomplish a one-time detailed visual inspection for corrosion of the wing rear spar lower girder area from WSTA 9270 to 11794, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-57- 049, dated March 24, 2015. (h) Modification of Wing Trailing Edge Within 1,000 flight cycles or 12 months, whichever occurs first after the effective date of this AD, modify the wing trailing edge lower skin panels into access panels, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100- 57-049, dated March 24, 2015. (i) Inspection of the Wing Rear Spar Lower Girder From WSTA 2635 to 8700 and WSTA 11794 to 12975 Within 2,000 flight cycles or 24 months, whichever occurs first after the effective date of this AD, accomplish a one-time detailed visual inspection for corrosion of the wing rear spar lower girder area from WSTA 2635 to 8700 and WSTA 11794 to 12975, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015. (j) Corrective Actions for the Inspections of Wing Rear Spar Lower Girder (1) If during any inspection required by paragraph (g) or (i) of this AD, as applicable, corrosion is found, before further flight, remove the corrosion and determine the remaining thickness at the damaged spots, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015. If the remaining thickness at the damaged spots, as determined by this paragraph, is not within the tolerances specified in Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, except as required by paragraph (k)(1) of this AD: Before further flight, accomplish the applicable corrective actions as defined in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, as applicable. (i) For corrosion damage found outboard of WSTA 8200 only: Repair, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-050, Revision 1, dated May 19, 2015. (ii) Repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Fokker Services B.V.'s EASA Design Organization Approval (DOA). (2) If during any inspection required by paragraph (g) or (i) of this AD, only damage to the surface protection is found, or if the remaining thickness at the damaged spots, as determined by paragraph (j)(1) of this AD, is within the tolerances specified in Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, except as required by paragraph (k)(1) of this AD: Before further flight, restore the surface protection, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57- 049, dated March 24, 2015, except as required by paragraph (k)(2) of this AD. (k) Exceptions to Service Information Specifications (1) Where Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, specifies the acceptability of smaller thickness or customized repairs: Before further flight, obtain acceptable tolerances, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Fokker Services B.V.'s EASA DOA. (2) Where Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, specifies contacting Fokker for a customized repair: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Fokker Services B.V.'s EASA DOA. (l) Reporting Requirements Submit a report of the findings, both positive and negative, of the inspections required by paragraphs (g) and (i) of this AD to Fokker Services, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-049, dated March 24, 2015, at the time specified in paragraph (l)(1) or (l)(2) of this AD. (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. (m) 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 EASA; or Fokker Service B.V.'s EASA 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. (n) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0113, dated June 22, 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-2016-7271. (o) 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 SBF100-57-049, dated March 24, 2015. (ii) Fokker Service Bulletin SBF100-57-050, Revision 1, dated May 19, 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. [[Page 87422]] (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 November 17, 2016. Phil Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-28601 Filed 12-2-16; 8:45 am] BILLING CODE 4910-13-P
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(2) You must use this service information ADDRESSES: For service information On an F28 Mark 0070 aeroplane, heavy
as applicable to do the actions required by identified in this final rule, contact, corrosion was found on the wing rear spar
this AD, unless this AD specifies otherwise. Fokker Services B.V., Technical lower girder. At small spots the effective
(i) Dassault Service Bulletin 7X–245, dated Services Dept., P.O. Box 1357, 2130 EL thickness of the vertical flange of the lower
June 8, 2015. girder was almost lost. Subsequently, a
(ii) Reserved.
Hoofddorp, the Netherlands; telephone number of inspections were accomplished on
(3) For service information identified in +31 (0)88–6280–350; fax +31 (0)88– other aeroplanes to provide additional
this AD, contact Dassault Falcon Jet 6280–111; email technicalservices@ information on possible corrosion in this
Corporation, Teterboro Airport, P.O. Box fokker.com; Internet http:// area. Because the rear spar lower girder
2000, South Hackensack, NJ 07606; www.myfokkerfleet.com. You may view between Wing Stations (WSTA) 9270 and
telephone 201–440–6700; Internet http:// this referenced service information at 11794 is hidden from view by the inboard
www.dassaultfalcon.com. the FAA, Transport Airplane and outboard aileron balancing plates, it is
(4) You may view this service information Directorate, 1601 Lind Avenue SW., possible that corrosion in this area remains
at the FAA, Transport Airplane Directorate, Renton, WA. For information on the undetected during the zonal inspections in
1601 Lind Avenue SW., Renton, WA. For zone 536 and 636 (MRB [Maintenance
information on the availability of this
availability of this material at the FAA, Review Board] tasks 062505–00–01 and
material at the FAA, call 425–227–1221. call 425–227–1221. It is also available 062605–00–01).The heavy corrosion was not
(5) You may view this service information on the Internet at http:// only found in the area between WSTA 9270
that is incorporated by reference at the www.regulations.gov by searching for and 11794, but also in the area where the rear
National Archives and Records and locating Docket No. FAA–2016– spar lower girder is directly visible.
Administration (NARA). For information on 7271. This condition, if not detected and
the availability of this material at NARA, call corrected, reduces the load carrying
202–741–6030, or go to: http:// Examining the AD Docket capability of the wing, possibly resulting in
www.archives.gov/federal-register/cfr/ibr- You may examine the AD docket on structural failure and loss of the aeroplane.
locations.html. the Internet at http:// To address this potential unsafe condition,
Fokker Services issued Service Bulletin (SB)
Issued in Renton, Washington, on www.regulations.gov by searching for SBF100–57–049 to provide instructions to
November 17, 2016. and locating Docket No. FAA–2016– detect and remove corrosion and to modify
Phil Forde, 7271; or in person at the Docket the wing trailing edge lower skin panels into
Acting Manager, Transport Airplane Management Facility between 9 a.m. access panels. SBF100–57–050 was issued to
Directorate, Aircraft Certification Service. and 5 p.m., Monday through Friday, provide repair instructions.
[FR Doc. 2016–28600 Filed 12–2–16; 8:45 am] except Federal holidays. The AD docket For the reasons described above, this
BILLING CODE 4910–13–P contains this AD, the regulatory [EASA] AD requires inspections of the
evaluation, any comments received, and affected areas and, depending on findings,
other information. The street address for accomplishment of applicable corrective
action(s) [including removing corrosion,
DEPARTMENT OF TRANSPORTATION the Docket Office (telephone 800–647– repair, and restoring protective finish]. This
5527) is Docket Management Facility, [EASA] AD also requires modification of the
Federal Aviation Administration U.S. Department of Transportation, wing trailing edge lower skin panels into
Docket Operations, M–30, West access panels [This modification is to
14 CFR Part 39 Building Ground Floor, Room W12–140, provide ease of access for later inspection
1200 New Jersey Avenue SE., and repairs in the affected areas.], and
[Docket No. FAA–2016–7271; Directorate
Washington, DC 20590. reporting of the results of the inspections to
Identifier 2015–NM–099–AD; Amendment
Fokker Services.
39–18722; AD 2016–24–05] FOR FURTHER INFORMATION CONTACT: Tom
More information on this subject can be
Rodriguez, Aerospace Engineer, found in Fokker Services All Operators
RIN 2120–AA64
International Branch, ANM 116, Message AOF100.197.
Airworthiness Directives; Fokker Transport Airplane Directorate, FAA,
You may examine the MCAI in the
Services B.V. Airplanes 1601 Lind Avenue SW., Renton, WA
AD docket on the Internet at http://
98057–3356; telephone 425–227–1137;
AGENCY: Federal Aviation www.regulations.gov by searching for
fax 425–227–1149.
Administration (FAA), Department of and locating Docket No. FAA–2016–
SUPPLEMENTARY INFORMATION: 7271.
Transportation (DOT).
Discussion Comments
ACTION: Final rule.
We issued a notice of proposed We gave the public the opportunity to
SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR participate in developing this AD. We
airworthiness directive (AD) for all part 39 by adding an AD that would received no comments on the NPRM or
Fokker Services B.V. Model F28 Mark apply to all Fokker Services B.V. Model on the determination of the cost to the
0070 and 0100 airplanes. This AD was F28 Mark 0070 and 0100 airplanes. The public.
prompted by heavy corrosion found on NPRM published in the Federal
the wing rear spar lower girder. This AD Register on June 23, 2016 (81 FR 40823) Conclusion
requires inspections of the affected (‘‘the NPRM’’). We reviewed the relevant data and
areas, modification of the wing trailing The European Aviation Safety Agency determined that air safety and the
edge lower skin panels, and corrective (EASA), which is the Technical Agent public interest require adopting this AD
actions if necessary. We are issuing this for the Member States of the European as proposed except for minor editorial
AD to address the unsafe condition on Union, has issued EASA Airworthiness changes. We have determined that these
sradovich on DSK3GMQ082PROD with RULES
these products. Directive 2015–0113, dated June 22, minor changes:
DATES: This AD is effective January 9, 2015 (referred to after this as the • Are consistent with the intent that
2017. Mandatory Continuing Airworthiness was proposed in the NPRM for
The Director of the Federal Register Information, or ‘‘the MCAI’’), to correct correcting the unsafe condition; and
approved the incorporation by reference an unsafe condition for all Fokker • Do not add any additional burden
of certain publications listed in this AD Services B.V. Model F28 Mark 0070 and upon the public than was already
as of January 9, 2017. 0100 airplanes. The MCAI states: proposed in the NPRM.
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Related Service Information Under 1 lower skin panels, and corrective or by the means identified in the
CFR Part 51 actions if necessary. We also reviewed ADDRESSES section.
Fokker Service Bulletin SBF100–57–
We reviewed Fokker Service Bulletin 050, Revision 1, dated May 19, 2015, Costs of Compliance
SBF100–57–049, dated March 24, 2015, which describes procedures for repair of We estimate that this AD affects 8
which describes procedures for an the wing spar. This service information airplanes of U.S. registry.
inspection for corrosion of certain wing is reasonably available because the
rear spar lower girder areas, interested parties have access to it We estimate the following costs to
modification of the wing trailing edge through their normal course of business comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Wing inspection and 35 work-hours × $85 per hour = $2,975 per in- $1,680 $4,655 per inspection $37,240 per inspection
modification. spection cycle. cycle. cycle.
Reporting ....................... 1 work hour × $85 per hour = $85 ..................... 0 85 ................................. 680.
We estimate the following costs to do the required inspection. We have no airplanes that might need these
any necessary corrective actions that way of determining the number of corrective actions:
will be required based on the results of
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Corrective Actions .................. Up to 372 work hours × $85 per hour = $31,620 ............... Up to $7,600 ......................... Up to $39,220.
Paperwork Reduction Act General requirements.’’ Under that List of Subjects in 14 CFR Part 39
A federal agency may not conduct or section, Congress charges the FAA with Air transportation, Aircraft, Aviation
sponsor, and a person is not required to promoting safe flight of civil aircraft in safety, Incorporation by reference,
respond to, nor shall a person be subject air commerce by prescribing regulations Safety.
to penalty for failure to comply with a for practices, methods, and procedures
the Administrator finds necessary for Adoption of the Amendment
collection of information subject to the
requirements of the Paperwork safety in air commerce. This regulation Accordingly, under the authority
Reduction Act unless that collection of is within the scope of that authority delegated to me by the Administrator,
information displays a current valid because it addresses an unsafe condition the FAA amends 14 CFR part 39 as
OMB control number. The control that is likely to exist or develop on follows:
number for the collection of information products identified in this rulemaking
required by this AD is 2120–0056. The action. PART 39—AIRWORTHINESS
paperwork cost associated with this AD DIRECTIVES
Regulatory Findings
has been detailed in the Costs of ■ 1. The authority citation for part 39
Compliance section of this document We determined that this AD will not continues to read as follows:
and includes time for reviewing have federalism implications under
instructions, as well as completing and Authority: 49 U.S.C. 106(g), 40113, 44701.
Executive Order 13132. This AD will
reviewing the collection of information. not have a substantial direct effect on § 39.13 [Amended]
Therefore, all reporting associated with the States, on the relationship between
this AD is mandatory. Comments ■ 2. The FAA amends § 39.13 by adding
the national government and the States,
concerning the accuracy of this burden the following new airworthiness
or on the distribution of power and
and suggestions for reducing the burden directive (AD):
responsibilities among the various
should be directed to the FAA at 800 levels of government. 2016–24–05 Fokker Services B.V.:
Independence Ave. SW., Washington, Amendment 39–18722; Docket No.
For the reasons discussed above, I FAA–2016–7271; Directorate Identifier
DC 20591, ATTN: Information certify that this AD:
Collection Clearance Officer, AES–200. 2015–NM–099–AD.
1. Is not a ‘‘significant regulatory (a) Effective Date
Authority for This Rulemaking action’’ under Executive Order 12866;
This AD is effective January 9, 2017.
Title 49 of the United States Code 2. Is not a ‘‘significant rule’’ under the
specifies the FAA’s authority to issue (b) Affected ADs
DOT Regulatory Policies and Procedures
rules on aviation safety. Subtitle I, (44 FR 11034, February 26, 1979); None.
section 106, describes the authority of (c) Applicability
sradovich on DSK3GMQ082PROD with RULES
the FAA Administrator. ‘‘Subtitle VII: 3. Will not affect intrastate aviation in
Aviation Programs,’’ describes in more Alaska; and This AD applies to all Fokker Services B.V.
4. Will not have a significant Model F28 Mark 0070 and 0100 airplanes,
detail the scope of the Agency’s certificated in any category.
authority. economic impact, positive or negative,
We are issuing this rulemaking under on a substantial number of small entities (d) Subject
the authority described in ‘‘Subtitle VII, under the criteria of the Regulatory Air Transport Association (ATA) of
Part A, Subpart III, Section 44701: Flexibility Act. America Code 57, Wings.
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![87422 Federal Register / Vol. 81, No. 233 / Monday, December 5, 2016 / Rules and Regulations
(5) You may view this service information email ac.yul@aero.bombardier.com; feed drain line, which can result in fuel
that is incorporated by reference at the Internet http://www.bombardier.com. leaking from the drain line. This
National Archives and Records You may view this referenced service condition, in combination with a nearby
Administration (NARA). For information on
information at the FAA, Transport hot surface or other potential ignition
the availability of this material at NARA, call
202–741–6030, or go to: http:// Airplane Directorate, 1601 Lind Avenue source, could result in an uncontrolled
www.archives.gov/federal-register/cfr/ibr- SW., Renton, WA. For information on fire in the aft equipment bay.
locations.html. the availability of this material at the Transport Canada Civil Aviation
Issued in Renton, Washington, on
FAA, call 425–227–1221. It is also (TCCA), which is the aviation authority
November 17, 2016. available on the Internet at http:// for Canada, has issued Canadian AD
Phil Forde,
www.regulations.gov by searching for CF–2015–26, dated August 31, 2015
and locating Docket No. FAA–2016– (referred to after this as the Mandatory
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
7418. Continuing Airworthiness Information,
[FR Doc. 2016–28601 Filed 12–2–16; 8:45 am] Examining the AD Docket or ‘‘the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.
BILLING CODE 4910–13–P You may examine the AD docket on Model CL–600–2A12 (CL–601 Variant)
the Internet at http:// and CL–600–2B16 (CL–601–3A, CL–
www.regulations.gov by searching for 601–3R, and CL–604 Variants)
DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2016– airplanes. The MCAI states:
Federal Aviation Administration 7418; or in person at the Docket
It was reported that a potential chaffing
Management Facility between 9 a.m.
condition exist between the Auxiliary Power
14 CFR Part 39 and 5 p.m., Monday through Friday, Unit (APU) negative-G fuel feed drain line
except Federal holidays. The AD docket and its surrounding structure and
[Docket No. FAA–2016–7418; Directorate contains this AD, the regulatory components. Leakage of the negative-G fuel
Identifier 2015–NM–163–AD; Amendment evaluation, any comments received, and feed drain line is a dormant failure, however,
39–18675; AD 2016–20–09] other information. The street address for in combination with a nearby hot surface or
RIN 2120–AA64 the Docket Office (telephone 800–647– other potential ignition source, could result
5527) is Docket Management Facility, in an uncontrolled fire in the aft equipment
Airworthiness Directives; Bombardier, U.S. Department of Transportation, bay.
Inc. Airplanes This [Canadian] AD mandates [for certain
Docket Operations, M–30, West
airplanes] the detailed visual inspection [for
AGENCY: Federal Aviation Building Ground Floor, Room W12–140, chafing conditions, e.g., fouling between the
Administration (FAA), Department of 1200 New Jersey Avenue SE., drain line and other components and
Transportation (DOT). Washington, DC 20590. insufficient clearance] and, if required,
FOR FURTHER INFORMATION CONTACT: rectification [corrective actions], to ensure
ACTION: Final rule.
Norman Perenson, Aerospace Engineer, required clearance between the APU
SUMMARY: We are adopting a new Propulsion and Services Branch, ANE– negative-G fuel feed drain line and its
airworthiness directive (AD) for certain surrounding structure and components [and,
173, FAA, New York Aircraft
for certain other airplanes, this [Canadian]
Bombardier, Inc. Model CL–600–2A12 Certification Office (ACO), 1600 Stewart AD mandates replacement of the APU
(CL–601 Variant), and CL–600–2B16 Avenue, Suite 410, Westbury, NY negative-G fuel feed tube assembly and the
(CL–601–3A, CL–601–3R, and CL–604 11590; telephone: 516–228–7337; fax: drain line].
Variants) airplanes. This AD was 516–794–5531.
prompted by a report that a potential Corrective actions include replacing
SUPPLEMENTARY INFORMATION:
chafing condition exists between the the APU negative-G fuel feed drain line.
negative-G fuel feed drain line of the Discussion You may examine the MCAI in the AD
auxiliary power unit (APU) and its We issued a notice of proposed docket on the Internet at http://
surrounding structure and components. rulemaking (NPRM) to amend 14 CFR www.regulations.gov by searching for
This AD requires, for certain airplanes, part 39 by adding an AD that would and locating Docket No. FAA–2016–
a detailed inspection for chafing apply to certain Bombardier, Inc. Model 7418.
conditions of the negative-G fuel feed CL–600–2A12 (CL–601 Variant), and Comments
drain line of the APU, and corrective CL–600–2B16 (CL–601–3A, CL–601–3R,
actions if necessary. For certain other and CL–604 Variants) airplanes. The We gave the public the opportunity to
airplanes, this AD requires replacement NPRM published in the Federal participate in developing this AD. We
of the APU negative-G fuel feed tube Register on June 28, 2016 (81 FR 41889) received no comments on the NPRM or
assembly and the drain line. We are (‘‘the NPRM’’). The NPRM was on the determination of the cost to the
issuing this AD to address the unsafe prompted by a report that a potential public.
condition on these products. chafing condition exists between the Conclusion
DATES: This AD is January 9, 2017. negative-G fuel feed drain line of the
The Director of the Federal Register APU and its surrounding structure and We reviewed the relevant data and
approved the incorporation by reference components. The NPRM proposed to determined that air safety and the
of certain publications listed in this AD require, for certain airplanes, a detailed public interest require adopting this AD
as of January 9, 2017. inspection for chafing conditions of the as proposed except for minor editorial
ADDRESSES: For service information negative-G fuel feed drain line of the changes. We have determined that these
sradovich on DSK3GMQ082PROD with RULES
identified in this final rule, contact APU, and corrective actions if minor changes:
Bombardier, Inc., 400 Côte-Vertu Road necessary. For certain other airplanes, • Are consistent with the intent that
West, Dorval, Québec H4S 1Y9, Canada; the NPRM proposed to require was proposed in the NPRM for
Widebody Customer Response Center replacement of the APU negative-G fuel correcting the unsafe condition; and
North America toll-free telephone 1– feed tube assembly and the drain line. • Do not add any additional burden
866–538–1247 or direct-dial telephone We are issuing this AD to prevent a upon the public than was already
1–514–855–2999; fax 514–855–7401; chafing condition in the negative-G fuel proposed in the NPRM.
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Document Created: 2016-12-03 00:26:10
Document Modified: 2016-12-03 00:26:10
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective January 9, 2017. | |
| 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 425-227-1149. | |
| FR Citation | 81 FR 87419 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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