AD 73-26-06

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AD Number:
73-26-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 727 Airplanes
Subject:
Corrosion Of Torsion Shafts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
The Boeing Company
Model:
727-100 Series | 727-100C Series | 727-200 Series | 727-200F Series | 727 Series | 727C Series
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 73-26-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1762

AD NUMBER:   73-26-06

SUBJECT HEADING:   BOEING Model 727 Airplanes

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
73-26-06 BOEING: Amdt. 39-1762. Applies to all Model 727 airplanes, certificated in all categories, listed in Boeing Service Bulletin 727-32-203, Revision 3, dated November 21, 1973, or later FAA approved revisions.
A. For reworked torsion shafts which were not plated in a manner to provide corrosion protection as specified in Boeing Service Bulletin 727-32-203, Revision 3, dated November 21, 1973, within the next 750 landings after the effective date of this AD, unless already accomplished within the last 750 landings, and thereafter at intervals not to exceed 1500 landings since the last such inspection, inspect the shafts for cracks in accordance with such service bulletin or later FAA approved revisions. Shafts found cracked are to be replaced prior to further flight with one of the following, any one of which is terminating action.
1) A shaft P/N 65-18949-1 which has never been reworked; or
2) A shaft P/N 65-18949-1 which has been reworked in accordance with Boeing Service Bulletin 727-32-203, Revision 3, dated November 21, 1973, or later FAA approved revisions; or
3) A shaft (P/N 65-18949-1) which has been reworked in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region; or
4) A newly designed shaft as specified in and installed in accordance with Boeing Service Bulletin 727-32-205, dated March 14, 1973, or later FAA approved revisions.
B. Prior to accumulation of 8,000 landings on a reworked torsion shaft which was not plated in a manner to provide corrosion protection, as specified in Boeing Service Bulletin 727- 32-203, Revision 3, dated November 21, 1973, or within the next 3,000 landings time in service after the effective date of this AD, whichever occurs later, replace the shaft with one of those described in A(1), A(2), A(3), or A(4).
C. For the purpose of this AD, when conclusive records are not available to show the number of landings accumulated by a particular shaft, the number of landings may be computed by dividing the airplane time in service since the shaft was installed in the airplane by the operator's fleet average time per flight for his Model 727 airplanes.
D. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering & Manufacturing Branch, FAA Northwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator, if the request contains substantiating data to justify the increase for that operator.

This Amendment becomes effective upon publication.

FOOTER: