AD 80-02-04

AD Final Rules - DRS_80-02-04.html
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AD Number:
80-02-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-9 Series Aircraft
Subject:
Aft Pressure Bulkhead Door
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/21/1980
Make:
The Boeing Company
Model:
DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-21 | DC-9-31 | DC-9-32 | DC-9-32 (...Show more
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Superseded AD: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Superseded By: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: 80-02-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3663

AD NUMBER:   80-02-04

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-9 Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective January 21, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-02-04 MCDONNELL DOUGLAS: Amendment 39-3663. Applicable to all Model DC-9 series aircraft equipped with non-ventral aft pressure bulkhead door, P/N 5910367, certificated in all categories.

Compliance required as indicated.

To detect cracks in the aft pressure bulkhead door, accomplish the following:

Within the next 25 landings, but not later than 72 elapsed hours, after the effective date of this AD, unless already accomplished in accordance with telegraphic AD T79WE-20 dated December 1, 1979, inspect the aft pressure bulkhead door as follows:

(a) Remove the door from the bulkhead.

(b) Remove all liner and insulation from the forward and aft sides of the door.

(c) Conduct a close visual inspection to detect cracks in the entire door structure including the web and doublers, paying particular attention to the areas adjacent to the inboard ends of the guide pin fittings (P/N 3913926).

(d) If cracks are found:

(1) Repair per FAA approved data and replace the insulation and liner removed in paragraph (b), or;

(2) The aircraft may be operated without cabin pressurization with a placard installed in the cockpit, in full view of the pilots stating: "Pressurized flight is prohibited."

(e) If no cracks are found, replace the insulation and liner removed in paragraph (b).

(f) Reinstall the door in the bulkhead.

(g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplanes unpressurized to a base where the inspections or crack repair can be performed.

(h) Within five working days after the inspection required by paragraph (c) of this AD, report the results of the inspection to the Chief, Aircraft Engineering Division, FAA Western Region. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.)

This amendment becomes effective January 21, 1980.


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