AD 80-02-16 R1

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AD Number:
80-02-16 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10, -30, and C-9 (Military) Series Airplanes
Subject:
Auxiliary Emergency Exit Door
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/14/1986
Make:
The Boeing Company
Model:
DC-9-11 | DC-9-12 | DC-9-13 | DC-9-14 | DC-9-15 | DC-9-15F | DC-9-31 | DC-9-32 | DC-9-32 (VC-9C) | D...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Superseded AD: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Superseded By: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: 80-02-16 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5438

AD NUMBER:   80-02-16 R1

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-9-10, -30, and C-9 (Military) Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 14, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-02-16 R1 MCDONNELL DOUGLAS: Amendment 39-3674 as amended by Amendment 39-5438. Applies to McDonnell Douglas Model DC-9-10, -30, and C-9 (Military) series airplanes, Fuselage Numbers 1 through 735, certificated in any category, equipped with the aft pressure bulkhead auxiliary emergency exit door (P/N 5910367).

Compliance required as indicated, unless already accomplished.

To detect fatigue cracks and prevent failure of the auxiliary emergency exit door, accomplish the following:

(a) Within 500 landings after the effective date of this AD and thereafter at intervals not to exceed 4,000 landings or one (1) year whichever comes first, inspect by x-ray each auxiliary emergency exit door shear pin fitting assembly in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A52-116, dated December 12, 1979.

(b) Any shear pin fitting assembly found cracked must be replaced with an FAA approved assembly prior to further flight.

(c) New shear pin fitting assemblies installed in accordance with paragraph (b), of the same type design, must be inspected initially before 20,000 landings after installation and thereafter at intervals not to exceed 4,000 landings or one (1) year whichever comes first, in accordance with paragraph (a).

(d) Accomplishment of modification in accordance with McDonnell Douglas DC-9 Service Bulletin 52-117, R1, dated October 6, 1982, or later FAA-approved revisions, constitutes terminating action for the repetitive inspection requirements of this AD.

(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD.

(f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(g) For the purposes of complying with this AD, subject to the acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the DC-9 airplane.

All persons affected by this directive who have not already received the appropriate documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.

Amendment 39-3674 became effective January 28, 1980.

This amendment, 39-5438, becomes effective November 14, 1986.


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