AD 89-11-06 R1

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AD Number:
89-11-06 R1
Document Type:
AD Final Rules
Docket Number:
88-NM-117-AD
Subject Heading:
Airworthiness Directives; BOEING Model 737 Series Airplanes
Subject:
Fuselage Skin Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/21/1990
Make:
The Boeing Company
Model:
737-100 Series | 737-200 Series | 737-200C Series | 737-300 Series | 737-400 Series | 737-500 Series...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Superseded AD: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Superseded By: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: 89-11-06 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   88-NM-117-AD

AMENDMENT:   39-6515

AD NUMBER:   89-11-06 R1

SUBJECT HEADING:   Airworthiness Directives; BOEING Model 737 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 21, 1990

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
89-11-06 R1 BOEING: Amendment 39-6219 as corrected by Amendment 39-6515. Docket No. 88-NM-117-AD.

Applicability: Model 737 series airplanes, listed in Boeing Alert Service Bulletin 737- 53A1027, Revision 3, dated December 2, 1983, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent failure of the forward lower cargo compartment frames, accomplish the following:

A. Except as provided by paragraph B., below, accomplish one of the following prior to the accumulation of 29,000 total landings or within the next 100 landings after June 22, 1989 (the effective date of Amendment 39-6219), whichever occurs later:

1. a. Unless previously accomplished within the last 200 landings, conduct a close external visual inspection of the fuselage skin for cracks in the region of the frames specified by Boeing Service Bulletin 737-53A1027, Revision 3, dated December 2, 1983. Reinspect at intervals not to exceed 300 landings until the frames are inspected in accordance with paragraph A.1.b., below. If cracks are found, prior to further flight, repair fuselage skin in accordance with an FAA-approved method and visually inspect the fuselage frames specified by the aforementioned service bulletin for cracks. Frames found cracked must be repaired prior to further flight, in accordance with the service bulletin.

b. Prior to the accumulation of 31,400 total landings, or within 100 landings after June 22, 1989 (the effective date of Amendment 39-6219), whichever occurs later, unless previously accomplished within the last 6,600 landings, and thereafter at intervals not to exceed 9,000 landings, conduct a visual inspection for cracks of the fuselage frames specified in paragraph A.1.a., above. If cracks are found, repair fuselage frames, prior to further flight, in accordance with Boeing Alert Service Bulletin 737-53A1027, Revision 3, dated December 2, 1983.

2. Unless previously accomplished within the last 1,900 landings, conduct an x- ray inspection for cracks of the fuselage frames specified in paragraph A.1.a., above, in accordance with procedures described in the Boeing Model 737 Nondestructive Test Manual D6- 37239, Part 2, Subject 53-10-16. Reinspect at intervals not to exceed 2,000 landings. If cracks are found, repair fuselage frames prior to further flight, in accordance with Boeing Alert Service Bulletin 737-53A1027, Revision 3, dated December 2, 1983.

3. Unless previously accomplished within the last 8,900 landings, perform an internal visual inspection for cracks of the fuselage frames specified in paragraph A.1.a., above. Reinspect at intervals not to exceed 9,000 landings. If cracks are found, repair fuselage frames prior to further flight, in accordance with Boeing Alert Service Bulletin 737-53A1027, Revision 3, dated December 2, 1983.

4. Unless previously accomplished within the last 8,900 landings, conduct a low frequency eddy current inspection for cracks of the fuselage frames specified in paragraph A.1.a., above, in accordance with procedures described in Boeing Model 737 Nondestructive Test Manual D6-37239, Part 6, Subject 53-10-01. Reinspect at intervals not to exceed 9,000 landings. If cracks are found, repair fuselage frames prior to further flight, in accordance with Boeing Alert Service Bulletin 737-53A1027, Revision 3, dated December 2, 1983.

B. For those airplanes that have been modified in accordance with Part III of Boeing Alert Service Bulletin 737-53A1027, Revision 3, dated December 2, 1983, or the terminating modification described in AD 81-13-08: Prior to the accumulation of 15,600 landings after modification or within the next 1,000 landings after June 22, 1989, (the effective date of Amendment 39-6219), whichever occurs later, perform the inspection described in paragraph A.3., above, and repeat thereafter at intervals not to exceed 15,600 landings. As an alternate to this repetitive inspection, the external inspection described in paragraph A.1.a., above, may be performed at intervals not to exceed 6,600 landings. If cracks are found, repair fuselage skins and frames prior to further flight, in accordance with Boeing Alert Service Bulletin 737- 53A1027, Revision 3, dated December 2, 1983, or in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. These repairs do not constitute terminating action and are subject to the repetitive inspection requirements of this paragraph.

C. For the purposes of complying with this AD, the number of landings may be determined to equal the number of pressurization cycles where the cabin pressure differential was greater than 2.0 PSI.

D. 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 will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office.

NOTE: Inspection and modification in accordance with Boeing Alert Service Bulletin 737-53A1027, Revision 4, dated July 13, 1984; Revision 5, dated February 1, 1985; and Revision 6, dated August 25, 1988; are acceptable alternate means of compliance for this AD.

E. 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. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.

Airworthiness Directive 89-11-06 superseded AD 81-13-08, Amendment 39-4141, which became effective on July 1, 1981.
The effective date of the requirements of this amendment remains June 22, 1989, as specified in Amendment 39-6219.
This correction (Amendment 39-6515, AD 89-11-06 R1) becomes effective on February 21, 1990.

FOOTER: