Aircraft Certification Staff Instruction (ACSI)

  REFERENCE NOTES
CF-82-11R1 DE HAVILLAND
Applies to all de Havilland of Canada Model DHC-7 Aircraft, Serial Numbers 1001 through 1100.

IDENTIFIER
Ref. Para 3.2.1

PRODUCT AFFECTED
Ref Para 3.2.2.

Compliance is required initially within 200 flight hours from the effective date of this Directive and thereafter at intervals not to exceed 500 flight hours. COMPLIANCE
Ref. Para 3.2.3 and 3.2.4
Cracking of Wing Root Rib strut members, (part number XRC1234) has occurred in service which, if left undetected, could result in catastrophic failure of the wing structure in flight. UNSAFE DESCRIPTION Ref. para 3.2.5 note simple, single sentence description of the problem.
To detect cracked Root Rib Strut members and prevent wing failure accomplish the following: CORRECTIVE ACTION
Ref. para 3.2.6 note - first sentence
  1. Visually inspect the top ends of the struts for cracks using a glass and strong light.
Gives simple description of what corrective action is trying to accomplish.
  1. X-Ray inspect for cracks the lower ends of the struts in accordance with the "Inspection Procedures" section of DHC Service Bulletin No. 07 dated 19 November 1932 or later approved revisions. Personnel accomplishing this inspection must be certified per Specification X1234.
Corrective Action options ref. para 3.2.7

Solid black line in R.H. Margin indicates where this revision differs from previous issue.

Use of Service Bulletin Ref para 3.2.8

  1. Replace struts found cracked in para a or b above with serviceable parts before returning the aircraft to service.
Modifications required ref. para 3.2.10
Alternate means of compliance with the requirements of this Directive may be used only if approved by the Director, Airworthiness Branch, Transport Canada Ottawa. Alternate Means of Compliance ref. para 3.2.12
This Directive supersedes the previous issue of this Directive CF-82-11 dated 19 November 1982. Superseding previous AD (in this case a previous issue) Ref. para 3.2.14
This Directive becomes effective 21 June 1985. Effectivity date ref. para 3.2.15
D.J. Doe Director, Airworthiness Branch for Minister of Transport Signature Ref. para 3.2.16
For further information regarding the contents or the interpretation of this Directive, contact your Regional Airworthiness Office, or call directly to M. (Authors Name), Transport Canada, Ottawa. Telephone (613) 990-0707. Paragraph to advise where assistance is available. ref. para 3.2.17

APPENDIX E

TRACKING SHEET: AIRWORTHINESS DIRECTIVES

DOCUMENT NUMBER ____________________________________________________

ORIGINATOR ____________________________________________________________

SUBJECT ________________________________________________________________

COORDINATED WITH ( YES / NO / N/A):

MANUFACTURERS OPERATORS REGION(S) FAA (etc)
       

SUPPLEMENTAL INFORMATION SHEET ENCLOSED: .......................................(  )

DRAFT REFERRED TO DATE INITIALS REMARKS
       
       
       
       

DIVISION CHIEFS ENDORSEMENT
(SIGNATURE & DATE, OR N/A)

AARDC AARDD AARDE AARDF OTHER
         

Note:

COMMENTS FROM INDIVIDUAL SECTIONS ENCLOSED.

FRENCH TRANSLATION VERIFIED BY: _____________________ DATE _________

EXECUTIVE SUMMARY ATTACHED: ....................................................................(  )

FINAL REFERRED TO DATE INITIALS REMARKS
       
       
       
       

TO MAIL ROOM ___________________________________________________________

APPENDIX F

AIRWORTHINESS DIRECTIVE SUMMARY - FORMAT

The AD Summary provides on one page essential information regarding the AD in the following format:

TITLE
(AD Number + Manufacturer + Model + Problem)
eg. CF-86-14 deHavilland DHC-7 Wing Fuel Leak

PRODUCT AFFECTED

This can be summary of the AD text eg "Applies to deHavilland of Canada Model DHC-7 aircraft, serial numbers 16 through 99 which have not had modification XYZ fitted.

BACKGROUND

This consists of a short description of the problem, specifying the number of occurances and significance of problem.

STATUS

State when the AD becomes effective. Give a short description as to how the AD has remedied the problem. Describe how AD action will terminate ti.e. with mod incorporation) or if further AD revisions are likely.

APPENDIX G

AIRWORTHINESS DIRECTIVE DEVELOPMENT


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