AD 2004-03-14 R1

AD Final Rules - 040314R1.pdf
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AD Number:
2004-03-14 R1
Document Type:
AD Final Rules
Docket Number:
2004-NM-38-AD
Subject Heading:
Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 S...Show more
Subject:
Rear Spar Fittings Between the Flex Shaft of the Flap Secondary Drive and the Wing-to-Fuselage Structure
Status:
Current
Citation:
Federal Register: May 11, 2004 (Volume 69, Number 91)
Citation Publish Date:
05/11/2004
Effective Date:
05/26/2004
Make:
Bombardier Inc.
Model:
DHC-8-102 | DHC-8-103 | DHC-8-106 | DHC-8-201 | DHC-8-202 | DHC-8-301 | DHC-8-311 | DHC-8-315
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
2004-03-14
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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1


[Federal Register: May 11, 2004 (Volume 69, Number 91)]


[Rules and Regulations]


[Page 26010-26012]


From the Federal Register Online via GPO Access [wais.access.gpo.gov]


[DOCID:fr11my04-9]


–––––––––––––––––––––––––––––––––––


DEPARTMENT OF TRANSPORTATION


Federal Aviation Administration


14 CFR Part 39


[Docket No. 2004-NM-38-AD; Amendment 39-13623; AD 2004-03-14 R1]


RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and


-315 Series Airplanes


AGENCY:
 
Federal Aviation Administration, DOT.


ACTION:
 
Final rule; request for comments.


–––––––––––––––––––––––––––––––––––


SUMMARY:
 
This amendment revises an existing airworthiness directive (AD), applicable to certain


Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series airplanes, that


currently requires repetitive inspections for discrepancies of certain rear spar fittings between the flex


shaft of the flap secondary drive and the wing-to-fuselage structure, and corrective action if


necessary. That AD also provides for an optional modification of the flex shaft installation, which


terminates the repetitive inspections. This amendment requires that the actions be done per approved


service information. The actions specified in this AD are intended to find and fix damage and prevent


subsequent failure of the rear spar fittings, which could result in loss of the wing. This action is


intended to address the identified unsafe condition.


DATES:
 
Effective May 26, 2004.


The incorporation by reference of certain publications listed in the regulations is approved by the


Director of the Federal Register as of May 26, 2004.


Comments for inclusion in the Rules Docket must be received on or before June 10, 2004.


ADDRESSES:
 
Submit comments in triplicate to the Federal Aviation Administration (FAA),


Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2004-NM-38-AD, 1601


Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location


between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays. Comments may be


submitted via fax to (425) 227-1232. Comments may also be sent via the Internet using the following


address: 9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must


contain ''Docket No. 2004-NM-38-AD'' in the subject line and need not be submitted in triplicate.


Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97


or 2000 or ASCII text.
2


The service information referenced in this AD may be obtained from Bombardier, Inc.,


Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5,


Canada. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind


Avenue, SW., Renton, Washington; at the FAA, New York Aircraft Certification Office, 1600


Stewart Avenue, suite 410, Westbury, New York; or 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/code_of_federal_regulations/ibr_locations.html
.


FOR FURTHER INFORMATION CONTACT:
 
Jon Hjelm, Aerospace Engineer, Airframe and


Propulsion Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue,


suite 410, Westbury, New York 11590; telephone (516) 228-7323; fax (516) 794-5531.


SUPPLEMENTARY INFORMATION:
 
On January 29, 2004, the FAA issued AD 2004-03-14,


amendment 39-13458 (69 FR 6139, February 10, 2004), applicable to certain Bombardier Model


DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series airplanes, to require repetitive


inspections for discrepancies of certain rear spar fittings between the flex shaft of the flap secondary


drive and the wing-to-fuselage structure, and corrective action if necessary. That action also provides


for an optional modification of the flex shaft installation, which terminates the repetitive inspections.


That action was prompted by reports of discrepancies of the rear spar fittings located between the flex


shaft of the flap secondary drive and the wing-to-fuselage structure. The requirements of that AD are


intended to find and fix damage and prevent subsequent failure of the rear spar fittings, which could


result in loss of the wing.


Actions Since Issuance of Previous Rule


Since the issuance of AD 2004-03-14, we have been advised that Bombardier Service Bulletin 8-


27-83, Revision `A', dated February 8, 2002, which was referenced as the appropriate source of


service information for the actions specified in the existing AD, was not approved by Transport


Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada. Subsequently,


Bombardier has issued Service Bulletin 8-27-83, Revision `A', dated May 29, 2002; which was


approved by TCCA. The procedures described in the approved service bulletin are almost identical to


those described in the earlier version of the service bulletin, with the exception of minor editorial


changes.


FAA's Findings


These airplane models are manufactured in Canada and are type certificated for operation in the


United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR


21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness


agreement, TCCA has kept us informed of the situation described above. We have examined the


findings of TCCA, reviewed all available information, and determined that AD action is necessary


for products of this type design that are certificated for operation in the United States.


Explanation of Requirements of Rule


Since an unsafe condition has been identified that is likely to exist or develop on other airplanes


of the same type design registered in the United States, this AD revises AD 2004-03-14 to continue to


require repetitive inspections for discrepancies of certain rear spar fittings between the flex shaft of


the flap secondary drive and the wing-to-fuselage structure, and corrective action if necessary. This