AD 71-09-04

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AD Number:
71-09-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 727 Airplanes
Subject:
Main Landing Gear Actuator Beam
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/28/1971
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Superseded AD: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Superseded By: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: 71-09-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1199

AD NUMBER:   71-09-04

SUBJECT HEADING:   BOEING Model 727 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 28, 1971.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
71-09-04 BOEING: Amdt. 39-1199. Applies to Model 727 airplanes listed in Boeing Service Bulletin 32-188, dated March 29, 1971, or later FAA approved revisions.
Compliance required as indicated.
To detect cracking of the main landing gear actuator beam, accomplish the following:
A. Unless already accomplished within the last 300 hours' time in service preceding the effective date of this AD, within the next 300 hours' time in service after the effective date of this AD or prior to the accumulation of 5300 hours' time in service, whichever occurs later, accomplish one of the following:
1. Visually inspect the main landing gear actuator beam for any evidence of cracking in accordance with Boeing Service Bulletin 32-188, dated March 29, 1971, or later FAA approved revision, or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. Repeat the visual inspection at intervals not to exceed 600 hours' time in service, or
2. Ultrasonically inspect the main landing gear actuator beam for cracks in accordance with Boeing Service Bulletin 32-188, dated March 29, 1971, or later FAA approved revision, or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. Repeat the ultrasonic inspection at intervals not to exceed 1500 hours' time in service.
B. If cracks are found replace the beam with a serviceable beam.
C. Where records maintained by the operator are such as will permit a clear determination of the number of hours' time in service accumulated by the main landing gear actuator beam, P/N 65-17658-11, installed on the airplane, the inspection times prescribed by this AD may be applied to the beam rather than to the airplane.
D. Inspections prescribed by this AD do not apply to new replacement beams, P/N 65- 57153-3, or to P/N 65-17658-11 beam until 5300 hours' time in service is reached.
E. Airplanes having cracked main landing gear actuator beams which require replacement under this AD may, in accordance with FAR 21.197, be flown with the landing gear extended to a base where the replacement can be accomplished.
This AD becomes effective May 28, 1971.

FOOTER: