AD 82-26-02

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AD Number:
82-26-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; ROCKWELL INTERNATIONAL Models NA 265-65, and NA 265-60 Series Airplanes
Subject:
Vertical Floor Panel Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/13/1983
Make:
Sabreliner Corporation
Model:
NA-265-60 | NA-265-65
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Superseded AD: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Superseded By: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: 82-26-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4610

AD NUMBER:   82-26-02

SUBJECT HEADING:   Airworthiness Directives; ROCKWELL INTERNATIONAL Models NA 265-65, and NA 265-60 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 13, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   82-26-02 ROCKWELL INTERNATIONAL: Amendment 39-4610. Applies to the Models NA 265-65, Serial Number 306-114, and NA 265-60 series airplanes, serial numbers 306- 1 through 306-141, except 306-114 and 306-136, certificated in any category. Compliance required as indicated unless already accomplished. To prevent a possible inadvertent cabin pressure loss due to fatigue failure of an interior pressure panel, accomplish the following:

A. Prior to the next flight visually inspect the vertical floor panel, P/N 306-312005-3, in accordance with the instructions provided in Rockwell International Sabreliner Service Bulletin (SB) 82-9.

1. If a crack is detected, replace the panel in accordance with the instructions in SB 82-9, prior to the next flight except for ferry flight per item C., below.

2. If no cracks are detected, repeat the inspections after the next 50 and 100 flight hours and replace if required.

B. Within the next 150 flight hours replace the panel in accordance with SB 82-9. Installation of the new panel constitutes terminating action per this AD.

C. Issuance of a special flight permit, in accordance with FAR 21.197, is permitted for the purpose of moving the affected airplanes to a repair station provided that for airplanes with a detected panel crack, the maximum altitude for the ferry flight must not exceed 25,000 feet with a cabin pressure differential not to exceed 5.0 p.s.i.

D. Alternative means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region.

This amendment becomes effective April 13, 1983, to all persons except those persons to whom it was made immediately effective by Emergency AD T82-26-02 letter dated December 26, 1982, which contained this amendment.

FOOTER: