AD 70-11-01

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AD Number:
70-11-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 747-100 Series Airplanes
Subject:
Wing Flap Support Arms
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/15/1970
Make:
The Boeing Company
Model:
747-100 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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 70-11-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1078

AD NUMBER:   70-11-01

SUBJECT HEADING:   BOEING Model 747-100 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 15, 1970.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
70-11-01 BOEING: Amdt. 39-992 as amended by Amendment 39-1078. Applies to Boeing Model 747-100 Series airplanes.
Compliance required within the next 40 flights after the effective date of this AD on aircraft having 960 or more flights, and thereafter at intervals not to exceed 40 flights from the last inspection.
To detect cracking in the wing trailing edge aft flap support arms of Boeing Model 747-100 series airplanes accomplish the following or an alternate procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(a) Inspect the wing trailing edge aft flap support arms for cracks in accordance with Boeing Alert Service Bulletin No. 27-2024, or later FAA approved revision.
(b) If no crack is found, repeat the inspection for cracks at intervals not to exceed 40 flights.
(c) If crack is found:
(1) and the crack length is 0.4 inches or greater, replace flap support arm with a serviceable part of the same part number in accordance with Boeing ASB 27-2024 (or later FAA approved revision) before further flight. After replacement repeat visual inspection per (b).
(2) and the crack length is less than 0.4 inches, the part may be continued in service provided that no more than one cracked support arm per flap panel exists. Parts so continued in service must be inspected at intervals not to exceed 20 flights, subject to the provisions of (c)(1) above.
(d) Repetitive inspections may be discontinued upon replacement of the existing aft flap support arm assemblies with new, improved support arm assemblies per Boeing Service Bulletin No. 27-7024, revision 2, or later FAA approved revision. Replacement of an existing support arm assembly with the new improved support arm assembly eliminates inspection requirement at that location only.
Amendment 39-992 effective May 25, 1970.
This Amendment (39-1078) becomes effective September 15, 1970.

FOOTER: