AD 68-15-01

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AD Number:
68-15-01
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:
07/20/1968
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Superseded AD: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Superseded By: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: 68-15-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-624

AD NUMBER:   68-15-01

SUBJECT HEADING:   BOEING Model 727 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 20, 1968.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-15-01 BOEING: Amendment 39-624. Applies to Model 727 Series airplanes listed in Parts I, II, and III of paragraph I, Planning Information . . . , 1. Airplanes Affected, of Boeing Service Bulletin No. 55-18(R-6) dated June 15, 1967, as set forth on pages 1 and 2 thereof, and hereafter referred to as Part I of 1. Airplanes Affected or Part II and Part III of 1. Airplanes Affected.

Compliance required as indicated.

To detect cracks or to prevent further cracks in the lower chord of the horizontal stabilizer rear spar, accomplish the following:

(a) Unless already accomplished within the last 750 hours' time in service, within the next 50 hours' time in service after the effective date of this AD or prior to 650 hours' time in service after April 10, 1966, whichever is later, and thereafter at intervals not to exceed 800 hours' time in service, inspect Model 727 Series airplanes with 350 or more hours' time in service on April 10, 1966, listed in Part I of 1. Airplanes Affected in accordance with paragraph (e) hereof.

(b) Unless already accomplished within the last 750 hours' time in service, within the next 50 hours' time in service after the effective date of this AD or prior to the accumulation of 1,000 hours' time in service, whichever is later, and thereafter at intervals not to exceed 800 hours' time in service, inspect Model 727 Series airplanes with less than 350 hours' time in service on April 10, 1966, listed in Part I of 1. Airplanes Affected, in accordance with paragraph (e) hereof.

(c) Unless already accomplished within the last 100 hours' time in service, within the next 700 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 800 hours' time in service, inspect Model 727 Series airplanes with 2,300 or more hours' time in service on the effective date of this AD listed in Part II and Part III of 1. Airplanes Affected in accordance with paragraph (e) hereof.

(d) Unless already accomplished within the last 100 hours' time in service, before the accumulation of 3,000 hours' time in service, and thereafter at intervals not to exceed 800 hours' time in service, inspect Model 727 Series airplanes with less than 2,300 hours' time in service on the effective date of this AD listed in Part II and Part III of 1. Airplanes Affected in accordance with paragraph (e) hereof.

(e) Visually inspect for cracks in the lower chord of the horizontal stabilizer rear spar, Stabilizer Stations 110.00 through 225.54, in accordance with Paragraph II, Accomplishment Instructions, Part I - Inspection Data, of Boeing Service Bulletin No. 55-18(R-2); dated January 3, 1966, or later FAA approved revision.

(f) If cracks are found, repair before further flight (except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed) in accordance with Paragraph II, Accomplishment Instructions, Part III - Repair Data, of Boeing Service Bulletin No. 55-18(R-2), dated January 3, 1966, or later FAA approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. After the repair is accomplished, the repetitive inspections required by this AD may be discontinued for areas repaired.

(g) If cracks are not found, the aircraft may be modified in accordance with Paragraph II, Accomplishment Instructions, Part II - Preventive Modification Data, of Boeing Service Bulletin No. 55-18(R-2) or later FAA approved revision. After the modification is accomplished, the repetitive inspections required by this AD may be discontinued for areas modified.

NOTE: A repair in accordance with Service Bulletin 55-18 or 55-18(R-1) is considered a preventive modification.

(h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Regional Director, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

This supersedes Amendment 39-208 (31 F. R. 4283), AD 66-07-02.

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. 522(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Company, Commercial Airplane Division, Post Office Box 707, Renton, Washington 98055. These documents may also be examined at Room 406, Building A, FAA Western Region Office, 5651 West Manchester Avenue, Los Angeles, California 90045 and FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. An historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region.

This amendment becomes effective July 20, 1968.

FOOTER: