AD 71-26-01

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AD Number:
71-26-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
BOEING Model 727 Series Airplanes
Subject:
Main Landing Gear Actuator Beam
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/04/1972
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Superseded AD: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Superseded By: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: 71-26-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1387

AD NUMBER:   71-26-01

SUBJECT HEADING:   BOEING Model 727 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 4, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
71-26-01 BOEING: Amdt. 39-1362 as amended by Amendment 39-1387. Applies to Model 727 series airplanes listed in Boeing Service Bulletin 32-196, dated 16 September 1971, and Revision 1, dated 24 November 1971, or later FAA approved revisions, incorporating main landing gear actuator beam support link shaft P/N 69-19167-1 and -2.

Compliance required as indicated:
To detect cracks in the main landing gear actuator beam support link shaft, accomplish the following:

(a) For all shafts which have accumulated 12,000 or more landing cycles on or after 25 January 1972, inspect the shaft within the next 1000 landings after 25 January 1972, unless already accomplished within the last 1000 landings, and thereafter at intervals not to exceed 2000 landings since the last inspection, per (b) below, until the shaft is replaced or reworked per (c) and (d) below.
(b) Inspect the shaft in accordance with Boeing Service Bulletin 32-196, Revision 1, dated 24 November 1971, or later FAA approved revisions, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA, Western Region. If evidence of a crack is found, replace the shaft, prior to further flight, with shaft P/N 69-19167-3 or with a shaft that (1) has accumulated less than 12,000 landing cycles, or (2) has been previously inspected per this AD, and found to be uncracked, or (3) has been reworked per (c) below.
(c) Rework or replace shafts per Boeing Service Bulletin 32-196, Revision 1, dated 24 November 1971, or later FAA approved revisions, or an equivalent rework approved by the Chief, Aircraft Engineering Division, FAA, Western Region.
(d) Within 16,000 landings after such rework per (c) above, replace all shafts with acceptable shafts as identified in (b) above. Identify the shafts replaced so as to prevent inadvertent return to service.
(e) For the purpose of this AD, when conclusive records are not available to show the number of landings accumulated by a particular shaft, the number of landings may be computed by dividing the airplane time in service since the shaft was installed in the airplane by the operator's fleet average time per flight for his model 727 airplanes.
(f) Inspections prescribed by this AD do not apply to new replacement shafts P/N 69- 19167-3 installed on Boeing 727 aircraft.

Amendment 39-1362 became effective January 25, 1972.
This Amendment 39-1387 becomes effective February 4, 1972.

FOOTER: