81 FR 45995 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 136 (July 15, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 136 (July 15, 2016)
| Page Range | 45995-45997 | |
| FR Document | 2016-16732 |
[Federal Register Volume 81, Number 136 (Friday, July 15, 2016)] [Proposed Rules] [Pages 45995-45997] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-16732] [[Page 45995]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8178; Directorate Identifier 2015-NM-197-AD] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This proposed AD was prompted by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. This proposed AD would require repetitive inspections of the external surface of the fuselage skin panel for loose or working fasteners, and corrective action if necessary; a detailed visual inspection of the longeron joint fittings for the existence of shims and, if necessary, repetitive inspections of the longeron and the longeron joint fittings for any cracking, and corrective action if necessary. This proposed AD would also provide terminating action for certain repetitive inspections. We are proposing this AD to detect and correct missing shims between the longerons and longeron joint fittings. Such missing shims could result in a gapping condition and lead to stress corrosion cracking of the longeron joint fittings, and could adversely affect the structural integrity of the wing-to-fuselage attachment joints. DATES: We must receive comments on this proposed AD by August 29, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. 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 NPRM, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375- 4539; 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. 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- 8178; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8178; Directorate Identifier 2015-NM-197-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF- 2015-22, dated August 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Bombardier, Inc. Model DHC-8-400 series airplanes. The MCAI states: The aeroplane manufacturer has determined that shims may not have been installed between the longerons and longeron joint fittings at fuselage station X373-380, stringers 7 on the left and right hand side, on certain aeroplanes. The missing shims could result in a gapping condition and could lead to stress corrosion cracking of the longeron joint fittings. Failure of the longeron joint fitting could compromise the structural integrity of the wing-to-fuselage attachment joint. This [Canadian] AD mandates inspections in the area of the longeron joint fittings. Corrective actions include replacing any loose or working fasteners (fasteners that show signs of wear or fatigue corrosion), repairing any structural damage, and replacing any cracked longeron or longeron with an amplitude of 50% or more of the calibration signal. 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-2016-8178. Related Service Information Under 1 CFR Part 51 Bombardier, Inc. has issued Bombardier Service Bulletin 84-53-65, dated February 27, 2015. The service information describes procedures for inspections of the external surface of the fuselage skin panel for loose or working fasteners; a detailed visual inspection of the longeron joint fittings for the existence of shims; high frequency eddy current (HFEC) inspections of the longeron and the longeron joint fittings for any cracking; and replacement of longeron fittings, shims, and fasteners. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe [[Page 45996]] condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 76 airplanes of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $12,920, or $170 per product. In addition, we estimate that any necessary follow-on actions would take about 3 work-hours for the inspection for missing shims, 9 work- hours for the replacement of longeron fittings and shims, and 1 work- hour for a reporting requirement; and would require parts costing $3,222; for a cost of up to $4,327 per product. We have no way of determining the number of aircraft that might need these actions. We have received no definitive data that would enable us to provide cost estimates for repair of loose or working fasteners or structural damage specified in this proposed AD. 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 proposed AD is 2120-0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, part A, subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Bombardier, Inc.: Docket No. FAA-2016-8178; Directorate Identifier 2015-NM-197-AD. (a) Comments Due Date We must receive comments by August 29, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and - 402 airplanes, certificated in any category, serial numbers 4156 through 4453 inclusive, 4456, and 4457. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a determination by the manufacturer that shims might not have been installed between the longerons and longeron joint fittings at station X373-380, stringer 7, on the left and right sides of the airplane. We are issuing this AD to detect and correct missing shims between the longerons and longeron joint fittings. Such missing shims could result in a gapping condition and lead to stress corrosion cracking of the longeron joint fittings, and could adversely affect the structural integrity of the wing-to- fuselage attachment joints. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the External Surface of the Fuselage Skin Panels At the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, do a detailed visual inspection of the external surface of the fuselage skin panel for loose or working fasteners (fasteners that show signs of wear or fatigue corrosion) and structural damage, in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, dated February 27, 2015. (1) For airplanes that have accumulated less than 10,000 total flight hours, or less than 5 years in service since new, as of the effective date of this AD: Prior to accumulating 12,000 total flight hours or 6 years in service since new, whichever occurs first. (2) For airplanes that have accumulated 10,000 total flight hours or more, or 5 years or more in service since new, as of the effective date of this AD: Within 2,000 flight hours or 12 months after the effective date of this AD, whichever occurs first. (h) Corrective Actions If any loose or working fastener or any structural damage is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO); and therafter do the inspections required by paragraph (i) of this AD. Accomplishment of a repair in accordance with a method approved by the Manager, New York ACO, FAA; or TCCA; or [[Page 45997]] Bombardier, Inc.'s TCCA DAO terminates the repetitive inspections required by paragraph (i) of this AD for the repaired area only. (i) Repetitive Detailed Visual Inspections Repeat the detailed visual inspection required by the introductory text to paragraph (g) of this AD at intervals not to exceed 12 months or 2,000 flight cycles, whichever occurs first after accomplishment of the most recent inspection, until the actions required by the introductory text to paragraph (j) of this AD are done. (j) Inspection for Missing Shims At the time specified in paragraph (j)(1) or (j)(2) of this AD, as applicable, do a detailed visual inspection of the longeron joint fittings for the existence of shims, in accordance with paragraph 3.C. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, dated February 27, 2015. (1) For airplanes that have accumulated less than 10,000 total flight hours, or less than 5 years in service since new, as of the effective date of this AD: Prior to accumulating 18,000 total flight hours or 9 years in service since new, whichever occurs first. (2) For airplanes that have accumulated 10,000 total flight hours or more, or 5 years or more in service since new, as of the effective date of this AD: Within 8,000 flight hours or 4 years after the effective date of this AD, whichever occurs first; but not to exceed 30,000 total flight hours or 144 months in service since new, whichever occurs first. (k) Airplanes With Installed Shims: No Further Action Required If the inspection required by the introductory text to paragraph (j) of this AD reveals that shims are installed in the longeron joint fittings, no further action is required by this AD. (l) Airplanes With Missing Shims: High Frequency Eddy Current (HFEC) Inspections and Corrective Actions If the inspection required by the introductory text to paragraph (j) of this AD reveals that any shim is missing from the longeron joint fittings: Before further flight, do an HFEC inspection of the longeron and the longeron joint fittings for any cracking, in accordance with paragraph 3.D. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, dated February 27, 2015. (1) If any crack is found, or any indication is found with an amplitude of 50% or more of the calibration signal: Before further flight, replace the longeron joint fittings, in accordance with paragraph 3.E. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, dated February 27, 2015. (2) After each inspection required by the introductory text to paragraph (l) and paragraph (l)(1) of this AD, report the inspection results at the applicable time specified in paragraph (l)(2)(i) or (l)(2)(ii) of this AD to Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-4539; email [email protected]; Internet http://www.bombardier.com. (i) If the inspection was done on or after the effective date of this AD: Within 30 days after that inspection. (ii) If the inspection was done before the effective date of this AD: Within 30 days after the effective date of this AD. (3) If any crack, or any indication with an amplitude of 50% or more of the calibration signal is not found: Repeat the HFEC inspection required by the introductory text to paragraph (l) of this AD at intervals not to exceed 12,000 flight hours or 6 years, whichever occurs first after accomplishment of the most recent HFEC inspection, in accordance with paragraph 3.D. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, dated February 27, 2015. If any crack is found, or any indication is found with an amplitude of 50% or more of the calibration signal: Before further flight, replace the longeron joint fittings, in accordance with paragraph 3.E. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, dated February 27, 2015. (m) Terminating Action for Repetitive HFEC Inspections Replacement of the longeron joint fittings, in accordance with paragraph 3.E. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, dated February 27, 2015, constitutes terminating action for the repetitive HFEC inspections required by paragraph (l)(3) of this AD. (n) 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 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s 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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF-2015-22, dated August 3, 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-2016-8178. (2) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-4539; email [email protected]; Internet http://www.bombardier.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on July 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-16732 Filed 7-14-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules 45995
DEPARTMENT OF TRANSPORTATION For service information identified in Airworthiness Directive CF–2015–22,
this NPRM, contact Bombardier, Inc., dated August 3, 2015 (referred to after
Federal Aviation Administration Q-Series Technical Help Desk, 123 this as the Mandatory Continuing
Garratt Boulevard, Toronto, Ontario Airworthiness Information, or ‘‘the
14 CFR Part 39 M3K 1Y5, Canada; telephone 416–375– MCAI’’), to correct an unsafe condition
[Docket No. FAA–2016–8178; Directorate 4000; fax 416–375–4539; email for certain Bombardier, Inc. Model
Identifier 2015–NM–197–AD] thd.qseries@aero.bombardier.com; DHC–8–400 series airplanes. The MCAI
Internet http://www.bombardier.com. states:
RIN 2120–AA64 You may view this referenced service The aeroplane manufacturer has
information at the FAA, Transport determined that shims may not have been
Airworthiness Directives; Bombardier,
Airplane Directorate, 1601 Lind Avenue installed between the longerons and longeron
Inc. Airplanes
SW., Renton, WA. For information on joint fittings at fuselage station X373–380,
AGENCY: Federal Aviation the availability of this material at the stringers 7 on the left and right hand side, on
Administration (FAA), DOT. FAA, call 425–227–1221. certain aeroplanes. The missing shims could
ACTION: Notice of proposed rulemaking result in a gapping condition and could lead
Examining the AD Docket to stress corrosion cracking of the longeron
(NPRM).
You may examine the AD docket on joint fittings.
SUMMARY: We propose to adopt a new the Internet at http:// Failure of the longeron joint fitting could
airworthiness directive (AD) for certain www.regulations.gov by searching for compromise the structural integrity of the
wing-to-fuselage attachment joint.
Bombardier, Inc. Model DHC–8–400 and locating Docket No. FAA–2016–
This [Canadian] AD mandates inspections
series airplanes. This proposed AD was 8178; or in person at the Docket in the area of the longeron joint fittings.
prompted by a determination by the Management Facility between 9 a.m.
manufacturer that shims might not have and 5 p.m., Monday through Friday, Corrective actions include replacing any
been installed between certain except Federal holidays. The AD docket loose or working fasteners (fasteners
longerons and longeron joint fittings. contains this proposed AD, the that show signs of wear or fatigue
This proposed AD would require regulatory evaluation, any comments corrosion), repairing any structural
repetitive inspections of the external received, and other information. The damage, and replacing any cracked
surface of the fuselage skin panel for street address for the Docket Operations longeron or longeron with an amplitude
loose or working fasteners, and office (telephone 800–647–5527) is in of 50% or more of the calibration signal.
corrective action if necessary; a detailed the ADDRESSES section. Comments will You may examine the MCAI in the AD
visual inspection of the longeron joint be available in the AD docket shortly docket on the Internet at http://
fittings for the existence of shims and, after receipt. www.regulations.gov by searching for
if necessary, repetitive inspections of FOR FURTHER INFORMATION CONTACT: Aziz and locating Docket No. FAA–2016–
the longeron and the longeron joint Ahmed, Aerospace Engineer, Airframe 8178.
fittings for any cracking, and corrective and Mechanical Systems Branch, ANE– Related Service Information Under 1
action if necessary. This proposed AD 171, FAA, New York Aircraft CFR Part 51
would also provide terminating action Certification Office (ACO), 1600 Stewart
for certain repetitive inspections. We are Avenue, Suite 410, Westbury, NY Bombardier, Inc. has issued
proposing this AD to detect and correct 11590; telephone 516–228–7329; fax Bombardier Service Bulletin 84–53–65,
missing shims between the longerons 516–794–5531. dated February 27, 2015. The service
and longeron joint fittings. Such missing SUPPLEMENTARY INFORMATION:
information describes procedures for
shims could result in a gapping inspections of the external surface of the
condition and lead to stress corrosion Comments Invited fuselage skin panel for loose or working
cracking of the longeron joint fittings, We invite you to send any written fasteners; a detailed visual inspection of
and could adversely affect the structural relevant data, views, or arguments about the longeron joint fittings for the
integrity of the wing-to-fuselage this proposed AD. Send your comments existence of shims; high frequency eddy
attachment joints. to an address listed under the current (HFEC) inspections of the
DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No. longeron and the longeron joint fittings
this proposed AD by August 29, 2016. FAA–2016–8178; Directorate Identifier for any cracking; and replacement of
ADDRESSES: You may send comments, 2015–NM–197–AD’’ at the beginning of longeron fittings, shims, and fasteners.
using the procedures found in 14 CFR your comments. We specifically invite This service information is reasonably
11.43 and 11.45, by any of the following comments on the overall regulatory, available because the interested parties
methods: economic, environmental, and energy have access to it through their normal
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will course of business or by the means
http://www.regulations.gov. Follow the consider all comments received by the identified in the ADDRESSES section.
instructions for submitting comments. closing date and may amend this FAA’s Determination and Requirements
• Fax: 202–493–2251. proposed AD based on those comments. of This Proposed AD
• Mail: U.S. Department of We will post all comments we
Transportation, Docket Operations, receive, without change, to http:// This product has been approved by
M–30, West Building Ground Floor, www.regulations.gov, including any the aviation authority of another
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Room W12–140, 1200 New Jersey personal information you provide. We country, and is approved for operation
Avenue SE., Washington, DC 20590. will also post a report summarizing each in the United States. Pursuant to our
• Hand Delivery: U.S. Department of substantive verbal contact we receive bilateral agreement with the State of
Transportation, Docket Operations, about this proposed AD. Design Authority, we have been notified
M–30, West Building Ground Floor, of the unsafe condition described in the
Room W12–140, 1200 New Jersey Discussion MCAI and service information
Avenue SE., Washington, DC, between 9 Transport Canada Civil Aviation referenced above. We are proposing this
a.m. and 5 p.m., Monday through (TCCA), which is the aviation authority AD because we evaluated all pertinent
Friday, except Federal holidays. for Canada, has issued Canadian information and determined an unsafe
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![45996 Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules
condition exists and is likely to exist or We are issuing this rulemaking under (a) Comments Due Date
develop on other products of the same the authority described in ‘‘Subtitle VII, We must receive comments by August 29,
type design. part A, subpart III, Section 44701: 2016.
General requirements.’’ Under that (b) Affected ADs
Costs of Compliance
section, Congress charges the FAA with
We estimate that this proposed AD None.
promoting safe flight of civil aircraft in
affects 76 airplanes of U.S. registry. air commerce by prescribing regulations (c) Applicability
We also estimate that it would take for practices, methods, and procedures This AD applies to Bombardier, Inc. Model
about 2 work-hours per product to the Administrator finds necessary for DHC–8–400, –401, and –402 airplanes,
comply with the basic requirements of safety in air commerce. This regulation certificated in any category, serial numbers
this proposed AD. The average labor is within the scope of that authority 4156 through 4453 inclusive, 4456, and 4457.
rate is $85 per work-hour. Based on because it addresses an unsafe condition (d) Subject
these figures, we estimate the cost of that is likely to exist or develop on
this proposed AD on U.S. operators to Air Transport Association (ATA) of
products identified in this rulemaking America Code 53, Fuselage.
be $12,920, or $170 per product. action.
In addition, we estimate that any (e) Reason
necessary follow-on actions would take Regulatory Findings This AD was prompted by a determination
about 3 work-hours for the inspection by the manufacturer that shims might not
We determined that this proposed AD
for missing shims, 9 work-hours for the have been installed between the longerons
would not have federalism implications and longeron joint fittings at station X373–
replacement of longeron fittings and
under Executive Order 13132. This 380, stringer 7, on the left and right sides of
shims, and 1 work-hour for a reporting
proposed AD would not have a the airplane. We are issuing this AD to detect
requirement; and would require parts
substantial direct effect on the States, on and correct missing shims between the
costing $3,222; for a cost of up to $4,327
the relationship between the national longerons and longeron joint fittings. Such
per product. We have no way of missing shims could result in a gapping
Government and the States, or on the
determining the number of aircraft that condition and lead to stress corrosion
distribution of power and
might need these actions. We have cracking of the longeron joint fittings, and
responsibilities among the various
received no definitive data that would could adversely affect the structural integrity
levels of government. of the wing-to-fuselage attachment joints.
enable us to provide cost estimates for
repair of loose or working fasteners or For the reasons discussed above, I
certify this proposed regulation: (f) Compliance
structural damage specified in this
1. Is not a ‘‘significant regulatory Comply with this AD within the
proposed AD. compliance times specified, unless already
action’’ under Executive Order 12866;
Paperwork Reduction Act done.
2. Is not a ‘‘significant rule’’ under the
A federal agency may not conduct or DOT Regulatory Policies and Procedures (g) Inspection of the External Surface of the
sponsor, and a person is not required to Fuselage Skin Panels
(44 FR 11034, February 26, 1979);
respond to, nor shall a person be subject 3. Will not affect intrastate aviation in At the time specified in paragraph (g)(1) or
to penalty for failure to comply with a (g)(2) of this AD, as applicable, do a detailed
Alaska; and visual inspection of the external surface of
collection of information subject to the
4. Will not have a significant the fuselage skin panel for loose or working
requirements of the Paperwork
economic impact, positive or negative, fasteners (fasteners that show signs of wear
Reduction Act unless that collection of or fatigue corrosion) and structural damage,
on a substantial number of small entities
information displays a current valid in accordance with paragraph 3.B. of the
under the criteria of the Regulatory
OMB control number. The control Accomplishment Instructions of Bombardier
Flexibility Act.
number for the collection of information Service Bulletin 84–53–65, dated February
required by this proposed AD is 2120– List of Subjects in 14 CFR Part 39 27, 2015.
0056. The paperwork cost associated (1) For airplanes that have accumulated
with this proposed AD has been Air transportation, Aircraft, Aviation less than 10,000 total flight hours, or less
detailed in the Costs of Compliance safety, Incorporation by reference, than 5 years in service since new, as of the
section of this document and includes Safety. effective date of this AD: Prior to
accumulating 12,000 total flight hours or 6
time for reviewing instructions, as well The Proposed Amendment years in service since new, whichever occurs
as completing and reviewing the first.
collection of information. Therefore, all Accordingly, under the authority (2) For airplanes that have accumulated
reporting associated with this proposed delegated to me by the Administrator, 10,000 total flight hours or more, or 5 years
AD is mandatory. Comments concerning the FAA proposes to amend 14 CFR part or more in service since new, as of the
the accuracy of this burden and 39 as follows: effective date of this AD: Within 2,000 flight
suggestions for reducing the burden hours or 12 months after the effective date of
PART 39—AIRWORTHINESS this AD, whichever occurs first.
should be directed to the FAA at 800
DIRECTIVES
Independence Ave. SW., Washington, (h) Corrective Actions
DC 20591, ATTN: Information ■ 1. The authority citation for part 39 If any loose or working fastener or any
Collection Clearance Officer, AES–200. continues to read as follows: structural damage is found during any
inspection required by this AD: Before
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701. further flight, repair using a method
Title 49 of the United States Code approved by the Manager, New York Aircraft
§ 39.13 [Amended] Certification Office (ACO), FAA; or Transport
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding Canada Civil Aviation (TCCA); or
the following new airworthiness Bombardier, Inc.’s TCCA Design Approval
section 106, describes the authority of Organization (DAO); and therafter do the
the FAA Administrator. ‘‘Subtitle VII: directive (AD): inspections required by paragraph (i) of this
Aviation Programs,’’ describes in more Bombardier, Inc.: Docket No. FAA–2016– AD. Accomplishment of a repair in
detail the scope of the Agency’s 8178; Directorate Identifier 2015–NM– accordance with a method approved by the
authority. 197–AD. Manager, New York ACO, FAA; or TCCA; or
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![Federal Register / Vol. 81, No. 136 / Friday, July 15, 2016 / Proposed Rules 45997
Bombardier, Inc.’s TCCA DAO terminates the email thd.qseries@aero.bombardier.com; collection of information displays a current
repetitive inspections required by paragraph Internet http://www.bombardier.com. valid OMB Control Number. The OMB
(i) of this AD for the repaired area only. (i) If the inspection was done on or after Control Number for this information
the effective date of this AD: Within 30 days collection is 2120–0056. Public reporting for
(i) Repetitive Detailed Visual Inspections after that inspection. this collection of information is estimated to
Repeat the detailed visual inspection (ii) If the inspection was done before the be approximately 5 minutes per response,
required by the introductory text to effective date of this AD: Within 30 days after including the time for reviewing instructions,
paragraph (g) of this AD at intervals not to the effective date of this AD. completing and reviewing the collection of
exceed 12 months or 2,000 flight cycles, (3) If any crack, or any indication with an information. All responses to this collection
whichever occurs first after accomplishment amplitude of 50% or more of the calibration of information are mandatory. Comments
of the most recent inspection, until the signal is not found: Repeat the HFEC concerning the accuracy of this burden and
actions required by the introductory text to inspection required by the introductory text suggestions for reducing the burden should
paragraph (j) of this AD are done. to paragraph (l) of this AD at intervals not to be directed to the FAA at: 800 Independence
exceed 12,000 flight hours or 6 years, Ave. SW., Washington, DC 20591, Attn:
(j) Inspection for Missing Shims whichever occurs first after accomplishment Information Collection Clearance Officer,
At the time specified in paragraph (j)(1) or of the most recent HFEC inspection, in AES–200.
(j)(2) of this AD, as applicable, do a detailed accordance with paragraph 3.D. of the
visual inspection of the longeron joint fittings Accomplishment Instructions of Bombardier (o) Related Information
for the existence of shims, in accordance Service Bulletin 84–53–65, dated February (1) Refer to Mandatory Continuing
with paragraph 3.C. of the Accomplishment 27, 2015. If any crack is found, or any Airworthiness Information (MCAI) Canadian
Instructions of Bombardier Service Bulletin indication is found with an amplitude of Airworthiness Directive CF–2015–22, dated
84–53–65, dated February 27, 2015. 50% or more of the calibration signal: Before August 3, 2015, for related information. This
(1) For airplanes that have accumulated further flight, replace the longeron joint MCAI may be found in the AD docket on the
less than 10,000 total flight hours, or less fittings, in accordance with paragraph 3.E. of Internet at http://www.regulations.gov by
than 5 years in service since new, as of the the Accomplishment Instructions of searching for and locating Docket No. FAA–
effective date of this AD: Prior to Bombardier Service Bulletin 84–53–65, dated 2016–8178.
accumulating 18,000 total flight hours or 9 February 27, 2015. (2) For service information identified in
years in service since new, whichever occurs this AD, contact Bombardier, Inc., Q-Series
first. (m) Terminating Action for Repetitive HFEC Technical Help Desk, 123 Garratt Boulevard,
(2) For airplanes that have accumulated Inspections Toronto, Ontario M3K 1Y5, Canada;
10,000 total flight hours or more, or 5 years Replacement of the longeron joint fittings, telephone 416–375–4000; fax 416–375–4539;
or more in service since new, as of the in accordance with paragraph 3.E. of the email thd.qseries@aero.bombardier.com;
effective date of this AD: Within 8,000 flight Accomplishment Instructions of Bombardier Internet http://www.bombardier.com. You
hours or 4 years after the effective date of this Service Bulletin 84–53–65, dated February may view this service information at the
AD, whichever occurs first; but not to exceed 27, 2015, constitutes terminating action for FAA, Transport Airplane Directorate, 1601
30,000 total flight hours or 144 months in the repetitive HFEC inspections required by Lind Avenue SW., Renton, WA. For
service since new, whichever occurs first. paragraph (l)(3) of this AD. information on the availability of this
material at the FAA, call 425–227–1221.
(k) Airplanes With Installed Shims: No (n) Other FAA AD Provisions
Further Action Required The following provisions also apply to this Issued in Renton, Washington, on July 8,
AD: 2016.
If the inspection required by the
introductory text to paragraph (j) of this AD (1) Alternative Methods of Compliance Michael Kaszycki,
reveals that shims are installed in the (AMOCs): The Manager, New York ACO, Acting Manager, Transport Airplane
longeron joint fittings, no further action is ANE–170, FAA, has the authority to approve Directorate, Aircraft Certification Service.
required by this AD. AMOCs for this AD, if requested using the [FR Doc. 2016–16732 Filed 7–14–16; 8:45 am]
procedures found in 14 CFR 39.19. In
(l) Airplanes With Missing Shims: High BILLING CODE 4910–13–P
accordance with 14 CFR 39.19, send your
Frequency Eddy Current (HFEC) Inspections request to your principal inspector or local
and Corrective Actions Flight Standards District Office, as
If the inspection required by the appropriate. If sending information directly DEPARTMENT OF TRANSPORTATION
introductory text to paragraph (j) of this AD to the ACO, send it to ATTN: Program
reveals that any shim is missing from the Manager, Continuing Operational Safety, Federal Aviation Administration
longeron joint fittings: Before further flight, FAA, New York ACO, 1600 Stewart Avenue,
do an HFEC inspection of the longeron and Suite 410, Westbury, NY 11590; telephone 14 CFR Part 39
the longeron joint fittings for any cracking, in 516–228–7300; fax 516–794–5531. Before [Docket No. FAA–2016–8177; Directorate
accordance with paragraph 3.D. of the using any approved AMOC, notify your Identifier 2015–NM–129–AD]
Accomplishment Instructions of Bombardier appropriate principal inspector, or lacking a
Service Bulletin 84–53–65, dated February principal inspector, the manager of the local RIN 2120–AA64
27, 2015. flight standards district office/certificate
(1) If any crack is found, or any indication holding district office. The AMOC approval Airworthiness Directives; Bombardier,
is found with an amplitude of 50% or more letter must specifically reference this AD. Inc. Airplanes
of the calibration signal: Before further flight, (2) Contacting the Manufacturer: For any
replace the longeron joint fittings, in requirement in this AD to obtain corrective AGENCY: Federal Aviation
accordance with paragraph 3.E. of the actions from a manufacturer, the action must Administration (FAA), DOT.
Accomplishment Instructions of Bombardier be accomplished using a method approved ACTION: Notice of proposed rulemaking
Service Bulletin 84–53–65, dated February by the Manager, New York ACO, ANE–170,
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(NPRM).
27, 2015. FAA; or TCCA; or Bombardier, Inc.’s TCCA
(2) After each inspection required by the DAO. If approved by the DAO, the approval SUMMARY: We propose to adopt a new
introductory text to paragraph (l) and must include the DAO-authorized signature. airworthiness directive (AD) for certain
paragraph (l)(1) of this AD, report the (3) Reporting Requirements: A federal
Bombardier, Inc. Model BD–700–1A10
inspection results at the applicable time agency may not conduct or sponsor, and a
specified in paragraph (l)(2)(i) or (l)(2)(ii) of person is not required to respond to, nor and BD–700–1A11 airplanes. This
this AD to Bombardier, Inc., Q-Series shall a person be subject to a penalty for proposed AD was prompted by a
Technical Help Desk, 123 Garratt Boulevard, failure to comply with a collection of determination that the existing
Toronto, Ontario M3K 1Y5, Canada; information subject to the requirements of instruction in a certain task in the
telephone 416–375–4000; fax 416–375–4539; the Paperwork Reduction Act unless that aircraft maintenance manual (AMM)
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Document Created: 2016-07-15 02:53:14
Document Modified: 2016-07-15 02:53:14
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 29, 2016. | |
| Contact | Aziz Ahmed, Aerospace 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 | 81 FR 45995 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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