82 FR 32620 - Airworthiness Directives; Bombardier, Inc., Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 135 (July 17, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 135 (July 17, 2017)
| Page Range | 32620-32622 | |
| FR Document | 2017-14698 |
[Federal Register Volume 82, Number 135 (Monday, July 17, 2017)] [Rules and Regulations] [Pages 32620-32622] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-14698] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0696; Directorate Identifier 2017-NM-070-AD; Amendment 39-18960; AD 2017-14-16] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc., Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD requires removing the fasteners attaching the machined center fitting to the rear spar frame lower flange splice, inspecting the fasteners and fastener holes for damage, reworking and repairing the fastener holes, as applicable, and replacing the fasteners. This AD was prompted by a report indicating that certain fasteners attaching the machined rear spar center fitting to the frame were installed with a gap between the fastener head and the structure, or were installed tilted. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective August 1, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 1, 2017. We must receive comments on this AD by August 31, 2017. 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. 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 final rule, contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; telephone: 514-855-5000; fax: 514-855-7401; email: [email protected]; Internet: http://www.bombardier.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-2017-0696. 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-2017- 0696; or in person at the Docket Operations office 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 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: Aziz Ahmed, Airframe Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-228-7329; fax: 516-794-5531. SUPPLEMENTARY INFORMATION: Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF-2017-12, dated March 10, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Bombardier, Inc. Model BD-100-1A10 airplanes. The MCAI states: During production, it was observed that some fasteners joining the machined rear spar center fitting were installed with a gap between the fastener head and the structure, and others were installed tilted. Improperly installed fasteners could cause a premature failure of the fitting fasteners and cracking within the fitting or frame, resulting in the loss of structural integrity of the wing to fuselage attachment. This [Canadian] AD mandates the removal of all fasteners at the rear spar frame lower flange splice, inspection and rework [and repair] of the holes, and fastener replacement with self-aligning fasteners and self-aligning collars. The inspections include a general visual inspection of the fasteners for damage (i.e., missing, broken, or deformed), and an eddy current inspection of the fastener holes for damage. Rework includes deburring and chamfering the holes. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0696. Related Service Information Under 1 CFR Part 51 Bombardier, Inc., has issued Service Bulletin 100-53-32, dated February 16, 2017. The service information describes procedures for removing and replacing the fasteners attaching the machined center fitting to the rear spar frame lower flange splice. The service information also describes procedures for inspecting the fasteners and fastener holes and reworking the fastener holes. 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 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 issuing this [[Page 32621]] AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. FAA's Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because improperly installed fasteners could cause premature failure of the fitting fasteners and cracking within the fitting or frame, resulting in reduced structural integrity of the wing-to-fuselage attachment. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0696; Directorate Identifier 2017-NM-070-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. Costs of Compliance We estimate that this AD affects 187 airplanes of U.S. registry. We also estimate that it will take about 37 work-hours 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 $15,150 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $3,437,060, or $18,380 per product. We have received no definitive data that would enable us to provide cost estimates for other on-condition actions specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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): 2017-14-16 Bombardier, Inc.: Amendment 39-18960; Docket No. FAA- 2017-0696; Directorate Identifier 2017-NM-070-AD. (a) Effective Date This AD becomes effective August 1, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., Model BD-100-1A10 airplanes, certificated in any category, serial numbers 20001 through 20433 inclusive. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report indicating that certain fasteners attaching the machined rear spar center fitting to the frame were installed with a gap between the fastener head and the structure, or were installed tilted. We are issuing this AD to prevent failure of the fitting fasteners and consequent cracking within the fitting or frame, which could result in reduced structural integrity of the wing-to-fuselage attachment. [[Page 32622]] (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement Before the accumulation of 7,500 total flight cycles, or within 10 days after the effective date of this AD, whichever occurs later, do the actions required by paragraphs (g)(1) through (g)(4) of this AD, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100-53-32, dated February 16, 2017. (1) Remove the fasteners attaching the machined center fitting (part number 1005340715), wing-to-fuselage attachment and splice fitting at fuselage station 587, to the rear spar frame lower flange splice. (2) Do a general visual inspection of the fasteners for damage and an eddy current inspection of the fastener holes for damage. (3) Rework the fastener holes as applicable. (4) Replace the fasteners with self-aligning fasteners and self- aligning collars. (h) Exception to Service Information Specifications If any damage of any fastener hole is found during any inspection required by paragraph (g)(2) of this AD, before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). (i) Reporting Submit a report of the findings of the inspections required by paragraph (g)(2) of this AD, as specified in Appendix 1 of Bombardier Service Bulletin 100-53-32, dated February 16, 2017, to [email protected], at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 10 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, New York ACO, ANE-170, 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 New York ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. 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, New York ACO, ANE-170, FAA; or TCCA; or the TCCA DAO. If approved by the DAO, the approval must include the DAO-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) Canadian Airworthiness Directive CF-2017-12, dated March 10, 2017, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0696. (2) For more information about this AD, contact Aziz Ahmed, Airframe Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-228-7329; fax: 516-794-5531. (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) Bombardier Service Bulletin 100-53-32, dated February 16, 2017. (ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; telephone: 514-855-5000; fax: 514- 855-7401; email: [email protected]; Internet: http://www.bombardier.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 July 6, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-14698 Filed 7-14-17; 8:45 am] BILLING CODE 4910-13-P
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physical discomfort to passengers or The Director of the Federal Register SUPPLEMENTARY INFORMATION:
cabin crew. approved the incorporation by reference
Discussion
(2) A significant transient may lead to of a certain publication listed in this AD
a significant reduction in safety as of August 1, 2017. Transport Canada Civil Aviation
margins, an increase in flightcrew We must receive comments on this (TCCA), which is the aviation authority
workload, discomfort to the flightcrew, AD by August 31, 2017. for Canada, has issued Canadian AD
or physical distress to the passengers or ADDRESSES: You may send comments, CF–2017–12, dated March 10, 2017
cabin crew, possibly including non-fatal using the procedures found in 14 CFR (referred to after this as the Mandatory
injuries. Significant transients do not 11.43 and 11.45, by any of the following Continuing Airworthiness Information,
require—in order to remain within or methods: or ‘‘the MCAI’’), to correct an unsafe
recover to the normal flight envelope— • Federal eRulemaking Portal: Go to condition for certain Bombardier, Inc.
any of the following: http://www.regulations.gov. Follow the Model BD–100–1A10 airplanes. The
(i) Exceptional piloting skill, instructions for submitting comments. MCAI states:
alertness, or strength. • Fax: 202–493–2251. During production, it was observed that
(ii) Forces applied by the pilot which • Mail: U.S. Department of some fasteners joining the machined rear
are greater than those specified in Transportation, Docket Operations, M– spar center fitting were installed with a gap
§ 23.143(c). between the fastener head and the structure,
30, West Building Ground Floor, Room
(iii) Accelerations or attitudes in the and others were installed tilted. Improperly
W12–140, 1200 New Jersey Avenue SE., installed fasteners could cause a premature
airplane that might result in further Washington, DC 20590. failure of the fitting fasteners and cracking
hazard to secured or non-secured • Hand Delivery: U.S. Department of within the fitting or frame, resulting in the
occupants. Transportation, Docket Operations, M– loss of structural integrity of the wing to
Issued in Kansas City, Missouri, on July 6, 30, West Building Ground Floor, Room fuselage attachment.
2017. W12–140, 1200 New Jersey Avenue SE., This [Canadian] AD mandates the removal
Washington, DC, between 9 a.m. and 5 of all fasteners at the rear spar frame lower
Kelly Broadway,
flange splice, inspection and rework [and
Acting Manager, Small Airplane Directorate p.m., Monday through Friday, except repair] of the holes, and fastener replacement
Aircraft Certification Service. Federal holidays. with self-aligning fasteners and self-aligning
[FR Doc. 2017–14938 Filed 7–14–17; 8:45 am] For service information identified in collars.
BILLING CODE 4910–13–P
this final rule, contact Bombardier, Inc.,
The inspections include a general
400 Côte-Vertu Road West, Dorval,
visual inspection of the fasteners for
Québec H4S 1Y9, Canada; telephone:
damage (i.e., missing, broken, or
DEPARTMENT OF TRANSPORTATION 514–855–5000; fax: 514–855–7401;
deformed), and an eddy current
email: thd.crj@aero.bombardier.com;
Federal Aviation Administration inspection of the fastener holes for
Internet: http://www.bombardier.com.
damage. Rework includes deburring and
You may view this referenced service
14 CFR Part 39 chamfering the holes.
information at the FAA, Transport
You may examine the MCAI on the
Airplane Directorate, 1601 Lind Avenue
[Docket No. FAA–2017–0696; Directorate Internet at http://www.regulations.gov
Identifier 2017–NM–070–AD; Amendment SW., Renton, WA. For information on
by searching for and locating Docket No.
39–18960; AD 2017–14–16] the availability of this material at the
FAA–2017–0696.
FAA, call 425–227–1221. It is also
RIN 2120–AA64 available on the Internet at http:// Related Service Information Under 1
www.regulations.gov by searching for CFR Part 51
Airworthiness Directives; Bombardier,
Inc., Airplanes and locating Docket No. FAA–2017– Bombardier, Inc., has issued Service
0696. Bulletin 100–53–32, dated February 16,
AGENCY: Federal Aviation 2017. The service information describes
Examining the AD Docket
Administration (FAA), DOT. procedures for removing and replacing
ACTION: Final rule; request for You may examine the AD docket on the fasteners attaching the machined
comments. the Internet at http:// center fitting to the rear spar frame
www.regulations.gov by searching for lower flange splice. The service
SUMMARY: We are adopting a new and locating Docket No. FAA–2017– information also describes procedures
airworthiness directive (AD) for certain 0696; or in person at the Docket for inspecting the fasteners and fastener
Bombardier, Inc., Model BD–100–1A10 Operations office between 9 a.m. and 5 holes and reworking the fastener holes.
airplanes. This AD requires removing p.m., Monday through Friday, except This service information is reasonably
the fasteners attaching the machined Federal holidays. The AD docket available because the interested parties
center fitting to the rear spar frame contains this AD, the regulatory have access to it through their normal
lower flange splice, inspecting the evaluation, any comments received, and course of business or by the means
fasteners and fastener holes for damage, other information. The street address for identified in the ADDRESSES section.
reworking and repairing the fastener the Docket Operations office (telephone
holes, as applicable, and replacing the 800–647–5527) is in the ADDRESSES FAA’s Determination and Requirements
fasteners. This AD was prompted by a section. Comments will be available in of This AD
report indicating that certain fasteners the AD docket shortly after receipt. This product has been approved by
attaching the machined rear spar center FOR FURTHER INFORMATION CONTACT: Aziz the aviation authority of another
jstallworth on DSK7TPTVN1PROD with RULES
fitting to the frame were installed with Ahmed, Airframe Engineer, Airframe country, and is approved for operation
a gap between the fastener head and the and Mechanical Systems Branch, ANE– in the United States. Pursuant to our
structure, or were installed tilted. We 171, FAA, New York Aircraft bilateral agreement with the State of
are issuing this AD to address the unsafe Certification Office (ACO), 1600 Stewart Design Authority, we have been notified
condition on these products. Avenue, Suite 410, Westbury, NY of the unsafe condition described in the
DATES: This AD becomes effective 11590; telephone: 516–228–7329; fax: MCAI and service information
August 1, 2017. 516–794–5531. referenced above. We are issuing this
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AD because we evaluated all pertinent According to the manufacturer, some responsibilities among the various
information and determined the unsafe of the costs of this AD may be covered levels of government.
condition exists and is likely to exist or under warranty, thereby reducing the For the reasons discussed above, I
develop on other products of the same cost impact on affected individuals. We certify that this AD:
type design. do not control warranty coverage for 1. Is not a ‘‘significant regulatory
affected individuals. As a result, we action’’ under Executive Order 12866;
FAA’s Determination of the Effective have included all costs in our cost
Date 2. Is not a ‘‘significant rule’’ under the
estimate. DOT Regulatory Policies and Procedures
An unsafe condition exists that
Paperwork Reduction Act (44 FR 11034, February 26, 1979);
requires the immediate adoption of this
A federal agency may not conduct or 3. Will not affect intrastate aviation in
AD. The FAA has found that the risk to
sponsor, and a person is not required to Alaska; and
the flying public justifies waiving notice
and comment prior to adoption of this respond to, nor shall a person be subject 4. Will not have a significant
rule because improperly installed to penalty for failure to comply with a economic impact, positive or negative,
fasteners could cause premature failure collection of information subject to the on a substantial number of small entities
of the fitting fasteners and cracking requirements of the Paperwork under the criteria of the Regulatory
within the fitting or frame, resulting in Reduction Act unless that collection of Flexibility Act.
reduced structural integrity of the wing- information displays a current valid List of Subjects in 14 CFR Part 39
to-fuselage attachment. Therefore, we OMB control number. The control
determined that notice and opportunity number for the collection of information Air transportation, Aircraft, Aviation
for public comment before issuing this required by this AD is 2120–0056. The safety, Incorporation by reference,
AD are impracticable and that good paperwork cost associated with this AD Safety.
cause exists for making this amendment has been detailed in the Costs of Adoption of the Amendment
effective in fewer than 30 days. Compliance section of this document
and includes time for reviewing Accordingly, under the authority
Comments Invited instructions, as well as completing and delegated to me by the Administrator,
This AD is a final rule that involves reviewing the collection of information. the FAA amends 14 CFR part 39 as
requirements affecting flight safety, and Therefore, all reporting associated with follows:
we did not precede it by notice and this AD is mandatory. Comments
opportunity for public comment. We PART 39—AIRWORTHINESS
concerning the accuracy of this burden
invite you to send any written relevant DIRECTIVES
and suggestions for reducing the burden
data, views, or arguments about this AD. should be directed to the FAA at 800 ■ 1. The authority citation for part 39
Send your comments to an address Independence Ave. SW., Washington, continues to read as follows:
listed under the ADDRESSES section. DC 20591, ATTN: Information
Include ‘‘Docket No. FAA–2017–0696; Collection Clearance Officer, AES–200. Authority: 49 U.S.C. 106(g), 40113, 44701.
Directorate Identifier 2017–NM–070– § 39.13 [Amended]
Authority for This Rulemaking
AD’’ at the beginning of your comments.
We specifically invite comments on the Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by adding
overall regulatory, economic, specifies the FAA’s authority to issue the following new airworthiness
environmental, and energy aspects of rules on aviation safety. Subtitle I, directive (AD):
this AD. We will consider all comments section 106, describes the authority of 2017–14–16 Bombardier, Inc.: Amendment
received by the closing date and may the FAA Administrator. ‘‘Subtitle VII: 39–18960; Docket No. FAA–2017–0696;
amend this AD based on those Aviation Programs,’’ describes in more Directorate Identifier 2017–NM–070–AD.
comments. detail the scope of the Agency’s
(a) Effective Date
We will post all comments we authority.
receive, without change, to http:// We are issuing this rulemaking under This AD becomes effective August 1, 2017.
www.regulations.gov, including any the authority described in ‘‘Subtitle VII, (b) Affected ADs
personal information you provide. We Part A, Subpart III, Section 44701: None.
will also post a report summarizing each General requirements.’’ Under that
substantive verbal contact we receive section, Congress charges the FAA with (c) Applicability
about this AD. promoting safe flight of civil aircraft in This AD applies to Bombardier, Inc.,
air commerce by prescribing regulations Model BD–100–1A10 airplanes, certificated
Costs of Compliance for practices, methods, and procedures in any category, serial numbers 20001
We estimate that this AD affects 187 the Administrator finds necessary for through 20433 inclusive.
airplanes of U.S. registry. safety in air commerce. This regulation (d) Subject
We also estimate that it will take is within the scope of that authority Air Transport Association (ATA) of
about 37 work-hours per product to because it addresses an unsafe condition America Code 53, Fuselage.
comply with the basic requirements of that is likely to exist or develop on
this AD and 1 work-hour per product for products identified in this rulemaking (e) Reason
reporting. The average labor rate is $85 action. This AD was prompted by a report
per work-hour. Required parts will cost indicating that certain fasteners attaching the
about $15,150 per product. Based on Regulatory Findings machined rear spar center fitting to the frame
jstallworth on DSK7TPTVN1PROD with RULES
these figures, we estimate the cost of We determined that this AD will not were installed with a gap between the
have federalism implications under fastener head and the structure, or were
this AD on U.S. operators to be installed tilted. We are issuing this AD to
$3,437,060, or $18,380 per product. Executive Order 13132. This AD will prevent failure of the fitting fasteners and
We have received no definitive data not have a substantial direct effect on consequent cracking within the fitting or
that would enable us to provide cost the States, on the relationship between frame, which could result in reduced
estimates for other on-condition actions the national government and the States, structural integrity of the wing-to-fuselage
specified in this AD. or on the distribution of power and attachment.
VerDate Sep<11>2014 14:51 Jul 14, 2017 Jkt 241001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\17JYR1.SGM 17JYR1](https://thefederalregister.org/doc/82_FR_32755/page/2.svg)
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(f) Compliance (2) Contacting the Manufacturer: For any the availability of this material at NARA, call
Comply with this AD within the requirement in this AD to obtain corrective 202–741–6030, or go to: http://
compliance times specified, unless already actions from a manufacturer, the action must www.archives.gov/federal-register/cfr/ibr-
done. be accomplished using a method approved locations.html.
by the Manager, New York ACO, ANE–170,
(g) Replacement Issued in Renton, Washington, on July 6,
FAA; or TCCA; or the TCCA DAO. If
2017.
Before the accumulation of 7,500 total approved by the DAO, the approval must
include the DAO-authorized signature. Dionne Palermo,
flight cycles, or within 10 days after the
effective date of this AD, whichever occurs (3) Reporting Requirements: A federal Acting Manager, Transport Airplane
later, do the actions required by paragraphs agency may not conduct or sponsor, and a Directorate, Aircraft Certification Service.
(g)(1) through (g)(4) of this AD, in accordance person is not required to respond to, nor [FR Doc. 2017–14698 Filed 7–14–17; 8:45 am]
with the Accomplishment Instructions of shall a person be subject to a penalty for BILLING CODE 4910–13–P
Bombardier Service Bulletin 100–53–32, failure to comply with a collection of
dated February 16, 2017. information subject to the requirements of
(1) Remove the fasteners attaching the the Paperwork Reduction Act unless that
DEPARTMENT OF TRANSPORTATION
machined center fitting (part number collection of information displays a current
1005340715), wing-to-fuselage attachment valid OMB Control Number. The OMB
Federal Aviation Administration
and splice fitting at fuselage station 587, to Control Number for this information
the rear spar frame lower flange splice. collection is 2120–0056. Public reporting for
(2) Do a general visual inspection of the this collection of information is estimated to 14 CFR Part 39
fasteners for damage and an eddy current be approximately 5 minutes per response, [Docket No. FAA–2016–9567; Directorate
inspection of the fastener holes for damage. including the time for reviewing instructions, Identifier 2016–NM–147–AD; Amendment
(3) Rework the fastener holes as applicable. completing and reviewing the collection of 39–18955; AD 2017–14–11]
(4) Replace the fasteners with self-aligning information. All responses to this collection
fasteners and self-aligning collars. of information are mandatory. Comments RIN 2120–AA64
concerning the accuracy of this burden and
(h) Exception to Service Information suggestions for reducing the burden should Airworthiness Directives; Airbus
Specifications be directed to the FAA at: 800 Independence Airplanes
If any damage of any fastener hole is found Ave. SW., Washington, DC 20591, Attn:
during any inspection required by paragraph Information Collection Clearance Officer, AGENCY: Federal Aviation
(g)(2) of this AD, before further flight, repair AES–200. Administration (FAA), Department of
using a method approved by the Manager, Transportation (DOT).
New York Aircraft Certification Office (ACO), (k) Related Information
ACTION: Final rule.
ANE–170, FAA; or Transport Canada Civil (1) Refer to Mandatory Continuing
Aviation (TCCA); or Bombardier, Inc.’s TCCA Airworthiness Information (MCAI) Canadian
SUMMARY: We are superseding
Design Approval Organization (DAO). Airworthiness Directive CF–2017–12, dated
March 10, 2017, for related information. You Airworthiness Directive (AD) 2007–13–
(i) Reporting may examine the MCAI on the Internet at 08, for certain Airbus Model A318,
Submit a report of the findings of the http://www.regulations.gov by searching for A319, A320, and A321 series airplanes.
inspections required by paragraph (g)(2) of and locating Docket No. FAA–2017–0696. AD 2007–13–08 required repetitive
this AD, as specified in Appendix 1 of (2) For more information about this AD, inspections of the auxiliary power unit
Bombardier Service Bulletin 100–53–32, contact Aziz Ahmed, Airframe Engineer, (APU) starter motor, APU inlet plenum,
dated February 16, 2017, to bbad_challenger_ Airframe and Mechanical Systems Branch, and APU air intake for discrepancies;
stress@aero.bombardier.com, at the ANE–171, FAA, New York ACO, 1600 repetitive cleaning of the APU air
applicable time specified in paragraph (i)(1) Stewart Avenue, Suite 410, Westbury, NY
intake; and applicable corrective
or (i)(2) of this AD. 11590; telephone: 516–228–7329; fax: 516–
(1) If the inspection was done on or after 794–5531. actions. This AD expands the
the effective date of this AD: Submit the applicability of AD 2007–13–08, and
report within 10 days after the inspection. (l) Material Incorporated by Reference includes an optional terminating
(2) If the inspection was done before the (1) The Director of the Federal Register installation for the repetitive actions.
effective date of this AD: Submit the report approved the incorporation by reference This AD was prompted by a
within 10 days after the effective date of this (IBR) of the service information listed in this determination that the unsafe condition
AD. paragraph under 5 U.S.C. 552(a) and 1 CFR could occur on additional airplanes. We
part 51.
(j) Other FAA AD Provisions are issuing this AD to address the unsafe
(2) You must use this service information
The following provisions also apply to this as applicable to do the actions required by condition on these products.
AD: this AD, unless this AD specifies otherwise. DATES: This AD is effective August 21,
(1) Alternative Methods of Compliance (i) Bombardier Service Bulletin 100–53–32, 2017.
(AMOCs): The Manager, New York ACO, dated February 16, 2017. The Director of the Federal Register
ANE–170, FAA, has the authority to approve (ii) Reserved. approved the incorporation by reference
AMOCs for this AD, if requested using the (3) For service information identified in of certain publications listed in this AD
procedures found in 14 CFR 39.19. In this AD, contact Bombardier, Inc., 400 Côte-
as of August 21, 2017.
accordance with 14 CFR 39.19, send your Vertu Road West, Dorval, Québec H4S 1Y9,
request to your principal inspector or local Canada; telephone: 514–855–5000; fax: 514– The Director of the Federal Register
Flight Standards District Office, as 855–7401; email: thd.crj@ approved the incorporation by reference
appropriate. If sending information directly aero.bombardier.com; Internet: http:// of certain other publications listed in
to the New York ACO, send it to ATTN: www.bombardier.com. this AD as of July 25, 2007 (72 FR
Program Manager, Continuing Operational (4) You may view this service information 33877, June 20, 2007).
jstallworth on DSK7TPTVN1PROD with RULES
Safety, FAA, New York ACO, 1600 Stewart at the FAA, Transport Airplane Directorate, ADDRESSES: For service information
Avenue, Suite 410, Westbury, NY 11590; 1601 Lind Avenue SW., Renton, WA. For
identified in this final rule, contact
telephone 516–228–7300; fax 516–794–5531. information on the availability of this
Before using any approved AMOC, notify material at the FAA, call 425–227–1221. Airbus, Airworthiness Office–EIAS, 1
your appropriate principal inspector, or (5) You may view this service information Rond Point Maurice Bellonte, 31707
lacking a principal inspector, the manager of that is incorporated by reference at the Blagnac Cedex, France; telephone: +33 5
the local flight standards district office/ National Archives and Records 61 93 36 96; fax: +33 5 61 93 44 51;
certificate holding district office. Administration (NARA). For information on email: account.airworth-eas@
VerDate Sep<11>2014 14:51 Jul 14, 2017 Jkt 241001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\17JYR1.SGM 17JYR1](https://thefederalregister.org/doc/82_FR_32755/page/3.svg)
Document Created: 2017-07-15 03:45:50
Document Modified: 2017-07-15 03:45:50
| 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; request for comments. | |
| Dates | This AD becomes effective August 1, 2017. | |
| Contact | Aziz Ahmed, Airframe Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-228-7329; fax: 516-794-5531. | |
| FR Citation | 82 FR 32620 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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