AD 2018-22-03

AD Final Rules - 2018-22-03.pdf
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AD Number:
2018-22-03
Document Type:
AD Final Rules
Docket Number:
FAA-2018-0160
Subject Heading:
Airworthiness Directives; Bombardier, Inc., Airplanes
Subject:
Stabilizers
Status:
Current
Citation:
Federal Register Volume 83, Number 206 (Wednesday, October 24, 2018)
Citation Publish Date:
10/24/2018
Effective Date:
11/28/2018
Make:
Bombardier Inc.
Model:
DHC-8-400 | DHC-8-401 | DHC-8-402
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
2016-24-03
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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[Federal Register Volume 83, Number 206 (Wednesday, October 24, 2018)]


[Rules and Regulations]


[Pages 53563-53567]


From the Federal Register Online via the Government Publishing Office [www.gpo.gov]


[FR Doc No: 2018-23031]


––––––––––––––––––––––––––––––––––


DEPARTMENT OF TRANSPORTATION


Federal Aviation Administration


14 CFR Part 39


[Docket No. FAA-2018-0160; Product Identifier 2017-NM-139-AD; Amendment 39-19476; AD


2018-22-03]


RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes


AGENCY:
 
Federal Aviation Administration (FAA), Department of Transportation (DOT).


ACTION:
 
Final rule.


––––––––––––––––––––––––––––––––––


SUMMARY:
 
We are superseding Airworthiness Directive (AD) 2016-24-03, which applied to


certain Bombardier, Inc., Model DHC-8-400 series airplanes. AD 2016-24-03 required repetitive


detailed inspections of barrel nuts and cradles, a check of the bolt torque of the preload indicating


(PLI) washers, and corrective actions if necessary. This AD retains the requirements of AD 2016-24-


03 and requires modifying the airplane by installing a sealing disk to a certain location and replacing


certain barrel nuts. This AD was prompted by reports of cracked and corroded barrel nuts found at


the mid-spar location of the horizontal-stabilizer-to-vertical-stabilizer attachment joint, and the


issuance of new service information that includes a terminal modification. We are issuing this AD to


address the unsafe condition on these products.


DATES:
 
This AD is effective November 28, 2018.


The Director of the Federal Register approved the incorporation by reference of certain


publications listed in this AD as of November 28, 2018.


The Director of the Federal Register approved the incorporation by reference of certain other


publications listed in this AD as of January 12, 2017 (81 FR 88623, December 8, 2016).


ADDRESSES:
 
For service information identified in this final rule, 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 thd.qseries@aero.bombardier.com; internet


http://www.bombardier.com. You may view this referenced service information at the FAA,


Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the


availability of this material at the FAA, call 206-231-3195. It is also available on the internet at


http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0160.
2


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-2018-0160; or in person at Docket Operations between 9 a.m. and 5


p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the


regulatory evaluation, any comments received, and other information. The address for Docket


Operations (phone: 800-647-5527) is 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:
 
Aziz Ahmed, Aerospace Engineer, Airframe and


Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY


11590; telephone 516-228-7329; fax 516-794-5531; email 9-avs-nyaco-cos@faa.gov.


SUPPLEMENTARY INFORMATION:


Discussion


We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD


2016-24-03, Amendment 39-18720 (81 FR 88623, December 8, 2016) (“AD 2016-24-03”). AD


2016-24-03 applied to certain Bombardier, Inc., Model DHC-8-400 series airplanes. The NPRM


published in the Federal Register on March 9, 2018 (83 FR 10408). The NPRM was prompted by


reports of cracked and corroded barrel nuts found at the mid-spar location of the horizontal-stabilizer-


to-vertical-stabilizer attachment joint, and the issuance of new service information that includes a


terminal modification. The NPRM proposed to continue to require repetitive detailed inspections of


each barrel nut and cradle, a check of the bolt torque of the PLI washers, and corrective action if


necessary. The NPRM also proposed to require modifying the airplane by installing a sealing disk to


a certain location and replacing certain barrel nuts. We are issuing this AD to address cracked and


corroded barrel nuts, which could compromise the structural integrity of the vertical-stabilizer


attachment joints and lead to loss of control of the airplane.


Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued


Canadian AD CF-2015-13R1, dated June 26, 2017 (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:


There has been one in-service report of a cracked and corroded barrel nut, part number


(P/N) DSC228-12, found at the mid-spar location of the horizontal stabilizer to


vertical stabilizer attachment joint. There have also been two other reports of corroded


barrel nuts found at mid-spar locations.


Preliminary investigation determined that the cracking is initiated by corrosion.


Further investigation confirmed that the corrosion was caused by inadequate cadmium


plating on the barrel nuts. Failure of the barrel nuts could compromise the structural


integrity of the joint and could lead to loss of control of the aeroplane.


The original version of this [Canadian] AD was issued to mandate the initial and


repetitive inspections of the barrel nuts [and cradles for cracks and corrosion] at each


of the horizontal stabilizer to vertical stabilizer attachment joints.


Revision 1 of this [Canadian] AD is issued to terminate the repetitive inspection


requirement by requiring the incorporation of a modification to install a sealing disc at


the middle spar location of the horizontal stabilizer to vertical stabilizer attachment