AD 74-10-08

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AD Number:
74-10-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 727 Series Airplanes
Subject:
Horizontal Stabilizer
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/27/1975
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Superseded AD: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Superseded By: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: 74-10-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2073

AD NUMBER:   74-10-08

SUBJECT HEADING:   BOEING Model 727 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 27, 1975.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
74-10-08 BOEING: Amendment 39-1836 as amended by Amendment 39-2073. Applies to all model 727 series airplanes certificated in all categories. Compliance required as indicated.
(A) Unless already accomplished on airplanes which have been delivered after September 30, 1973, or which have had new horizontal stabilizer hinge pins, P/N 69-14410, installed since that time, conduct the inspection and modification of paragraph (C) below, within the next 15 days after the effective date of this AD.
(B) Unless already accomplished on all other airplanes, conduct the inspection and modification of paragraph (C) below, within the next 6 months after the effective date of this AD.
(C) Inspect the horizontal stabilizer hinge pins for integrity, replace as necessary, and install threaded retention rods, P/N 69-67076, or equivalent, in accordance with Boeing Alert Service Bulletin 727-55-59, or FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
(D) If a threaded rod, P/N 69-67076-2, or an equivalent fabricated rod made from threaded rod NAS 1454-( )-( ), or any other rod with a Class 2 thread has been installed, unless already accomplished, conduct, before September 6, 1975, the hinge pin retainer nut torque inspection in accordance with Paragraph III, Part II of Boeing Alert Service Bulletin No. 727-55- 59, Revision 2, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
If the torque required to rotate the self-locking nut is less than 30 inch-pounds, replace the rod in accordance with Boeing Alert Service Bulletin No. 727-55-59, Revision 3, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.
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 may obtain copies upon request to The Boeing Company, P. O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, Boeing Field, Seattle, Washington.

Amendment 39-1836 became effective on May 10, 1974.
This Amendment 39-2073 becomes effective on February 27, 1975.

FOOTER: