AD 2000-02-07 R1

AD Final Rules - 000207R1.pdf
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AD Number:
2000-02-07 R1
Document Type:
AD Final Rules
Docket Number:
2003-NM-153-AD
Subject Heading:
Airworthiness Directives; Bombardier Model DHC-7-100 Series Airplanes
Subject:
Locking Pin Fittings of Baggage Door and Locking Pin Housings of Fuselage
Status:
Current
Citation:
Federal Register: May 11, 2004 (Volume 69, Number 91)
Citation Publish Date:
05/11/2004
Effective Date:
06/15/2004
Make:
Viking Air Limited
Model:
DHC-7-100 | DHC-7-101 | DHC-7-102 | DHC-7-103
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
2000-02-07
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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[Federal Register: May 11, 2004 (Volume 69, Number 91)]


[Rules and Regulations]


[Page 26025-26027]


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


[DOCID:fr11my04-18]


–––––––––––––––––––––––––––––––––––


DEPARTMENT OF TRANSPORTATION


Federal Aviation Administration


14 CFR Part 39


[Docket No. 2003-NM-153-AD; Amendment 39-13612; AD 2000-02-07 R1]


RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-7-100 Series Airplanes


AGENCY:
 
Federal Aviation Administration, DOT.


ACTION:
 
Final rule.


–––––––––––––––––––––––––––––––––––


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


Bombardier Model DHC-7-100 series airplanes, that currently requires repetitive high frequency


eddy current inspections to detect cracks on the locking pin fittings of the baggage door and locking


pin housings of the fuselage; repetitive detailed inspections to detect cracks of the inner door


structure on all four door locking attachment fittings; and corrective actions if necessary. In lieu of


accomplishing the corrective actions, that amendment also provides a temporary option, for certain


cases, for revising the Airplane Flight Manual and installing a placard. That AD was prompted by


issuance of mandatory continuing airworthiness information by a foreign civil airworthiness


authority. The actions specified by that AD are intended to detect and correct fatigue cracking of the


baggage door fittings and the support structure, which could result in structural failure, and


consequent rapid decompression of the airplane during flight. This amendment extends the


compliance time of the repetitive inspections based on test evidence and is intended to address the


identified unsafe condition.


DATES:
 
Effective June 15, 2004.


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


Director of the Federal Register as of June 15, 2004.


ADDRESSES:
 
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 Federal Aviation Administration (FAA), Transport


Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or 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
.
2


FOR FURTHER INFORMATION CONTACT:
 
David Lawson, 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) 228-7327; fax (516) 794-5531.


SUPPLEMENTARY INFORMATION:
 
A proposal to amend part 39 of the Federal Aviation


Regulations (14 CFR part 39) by revising AD 2000-02-07, amendment 39-11526 (65 FR 4354,


January 27, 2000), which is applicable to all Bombardier Model DHC-7-100 series airplanes, was


published in the Federal Register on January 29, 2004 (69 FR 4257). The action proposed to require


repetitive high frequency eddy current inspections to detect cracks on the locking pin fittings of the


baggage door and locking pin housings of the fuselage; repetitive detailed inspections to detect cracks


of the inner door structure on all four door locking attachment fittings; and corrective actions, if


necessary. In lieu of accomplishing the corrective actions, that amendment also provides a temporary


option, for certain cases, for revising the Airplane Flight Manual (AFM), and installing a placard.


That action was prompted by issuance of mandatory continuing airworthiness information by a


foreign civil airworthiness authority. The actions specified by that AD are intended to detect and


correct fatigue cracking of the baggage door fittings and the support structure, which could result in


structural failure, and consequent rapid decompression of the airplane during flight.


Comments


Interested persons have been afforded an opportunity to participate in the making of this


amendment. No comments were submitted in response to the proposal or the FAA's determination of


the cost to the public.


Change to Final Rule


We have changed paragraphs (b)(1) and (b)(2) of this final rule to specify that the actions shall


be done in accordance with a method approved by the Manager, New York Aircraft Certification


Office (ACO), FAA, Engine and Propeller Directorate, or the Transport Canada Civil Aviation (or its


delegated agent). In addition, the de Havilland Dash 7 Maintenance Manual PSM 1-7-2 is listed as


one approved method of compliance for accomplishment of the actions.


Conclusion


After careful review of the available data, we have determined that air safety and the public


interest require the adoption of the rule with the change described previously. This change will


neither increase the economic burden on any operator nor increase the scope of the AD.


Changes to 14 CFR Part 39/Effect on the AD


On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002),


which governs our airworthiness directives system. The regulation now includes material that relates


to altered products, special flight permits, and alternative methods of compliance (AMOCs).


However, for clarity and consistency in this final rule, we have retained the language of the NPRM


regarding that material.


Cost Impact


The changes in this action add no additional economic burden. The current costs for this AD are


repeated for the convenience of affected operators, as follows: