AD 76-18-11

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AD Number:
76-18-11
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 727-100 and 727-100C Series Airplanes
Subject:
Aft Cargo Door
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/18/1977
Make:
The Boeing Company
Model:
727-100 Series | 727-100C 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Superseded AD: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Superseded By: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: 76-18-11
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2808

AD NUMBER:   76-18-11

SUBJECT HEADING:   BOEING Model 727-100 and 727-100C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 18, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-18-11 BOEING: Amendment 39-2720 as amended by Amendment 39-2736 and 39-2771 is further amended by Amendment 39-2808. Applies to all Model 727-100 and 727-100C series airplanes, certificated in all categories, with P/N 65-19670-2 and -3 aft cargo door lowest side stop fittings which have accumulated 15,000 or more pressurization cycles. Compliance required as indicated.
To detect cracks in the aft cargo door lower stop fittings, accomplish the following:
A. Within the next 500 flights from the effective date of this amendment, unless accomplished within the last 500 flights, visually inspect the aft cargo door for cracks in the four (4) lowest side stop fittings (two forward and two aft) and the attaching door frame structure in accordance with Boeing Alert Service Bulletin No. 727-52-A102, Revision 2, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Repeat visual inspections of the lowest forward and aft side fittings (total of two) and adjacent door frame structure at intervals not to exceed 1000 flights from the last inspection.
B. If a cracked fitting(s) and/or frame(s) are detected:
1. replace the fitting and repair or replace the door frame section, as necessary, prior to further flight in accordance with Boeing Alert Service Bulletin No. 727-52-A102, Revision 1, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region; or
2. continue service with no more than one cracked fitting and/or frame for up to 50 flights under the following conditions:
a. frame cracks may not extend along the frame more than 4.5 inches, including the length of the stop fitting cutout, and no cracks may be present in the frame flange radius. Stop drill all frame cracks, which do not terminate in an existing fastener hole.
b. assure that the stop fittings adjacent to the cracked fitting, including the lower sill stop fitting, are crack-free by the visual inspection specified in the service bulletin.
c. within 25 flights repeat the visual inspection of the adjacent fittings and frame per a and b above.
d. within 50 flights replace the fitting with a crack-free 7079-T6 aluminum or steel fitting and repair or replace the door frame, as necessary, in accordance with the service bulletin.
C. Replacement of a lowest side stop fitting with a new steel fitting in accordance with Boeing Alert Service Bulletin No. 727-52-A102, Revision 2, or later FAA approved revisions, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, constitutes terminating action for this AD at that fitting, provided the adjacent fitting and attaching door frame were/are inspected and found to be crack-free in accordance with Revision 2 to the service bulletin or equivalent.
D. For the purpose of this AD, when conclusive records are not available to show the number of flights accumulated by a particular fitting, the number of flights may be computed by dividing the airplane time-in-service since the fitting was installed in the airplane by the operator's fleet average time per flight for his Model 727 airplanes.
E. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive inspection intervals in this AD, if the request contains substantiating data to justify the increase for that operator.
The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).
All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.

Amendment 39-2720 became effective September 21, 1976.
Amendment 39-2736 became effective October 15, 1976.
Amendment 39-2771 became effective November 29, 1976.
This amendment 39-2808 becomes effective February 18, 1977.

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