AD 89-23-07

AD Final Rules - DRS_89-23-07.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
89-23-07
Document Type:
AD Final Rules
Docket Number:
89-NM-63-AD
Subject Heading:
Airworthiness Directives; BOEING Model 747 Series Airplanes
Subject:
Steel Bolt Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/04/1989
Make:
The Boeing Company
Model:
747-100 Series | 747-100B Series | 747-100B SUD Series | 747-200B Series | 747-200C Series | 747-200...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Superseded AD: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Superseded By: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: 89-23-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   89-NM-63-AD

AMENDMENT:   39-6376

AD NUMBER:   89-23-07

SUBJECT HEADING:   Airworthiness Directives; BOEING Model 747 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 4, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
89-23-07 BOEING: Amendment 39-6376. Docket No. 89-NM-63-AD.

Applicability: Model 747 series airplanes, listed in Boeing Service Bulletin 747-51- 2043, dated June 30, 1988, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent structural damage caused by cracked or fractured H-11 steel bolts, accomplish the following:

A. Prior to the accumulation of 4 years total time-in-service, or within the next 15 months after the effective date of this AD, whichever occurs later, visually inspect H-11 steel bolts for cracks or fractures, in accordance with Boeing Service Bulletin 747-51-2043, dated June 30, 1988, at the following locations:

1. Body landing gear inboard and outboard trunnion vertical support.

2. Wing landing gear beam upper chord to longeron attachment.

3. Wing landing gear beam lower chord to crease beam attachment.

4. Body station (BS) 2598 horizontal stabilizer hinge attachment.

5. BS 2598 longeron splice fitting attachment at stringers 11 and 23.

6. Fin to body attachment.

7. The horizontal stabilizer front spar jack screw attachment.

B. If a cracked or fractured bolt is found, replace with an Inconel 718 bolt, prior to further flight, in accordance with Boeing Service Bulletin 747-51-2043, dated June 30, 1988.

C. If a cracked or fractured bolt is found and if Inconel 718 bolts are unavailable, replace the cracked or fractured bolt with an H-11 steel bolt, prior to further flight, in accordance with Boeing Service Bulletin 747-51-2043, dated June 30, 1988. Repeat the visual inspection required by paragraph A., above, at intervals not to exceed 18 months.

D. If no cracking or fracture is found, repeat the visual inspection required by paragraph A., above, at intervals not to exceed 18 months.

E. Within the next 48 months after the effective date of this AD, replace all affected H-11 steel bolts with Inconel 718 bolts, in accordance with Boeing Service Bulletin 747-51-2043, dated June 30, 1988.

F. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office.

G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. The documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

This amendment (39-6376, AD 89-23-07) becomes effective on December 4, 1989.

FOOTER: