AD 76-17-05

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AD Number:
76-17-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED-CALIFORNIA Model L-1011-385 Series Airplanes
Subject:
Electrical Wires
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/02/1976
Make:
Lockheed Martin Corporation
Model:
L-1011-385-1 | L-1011-385-1-14 | L-1011-385-1-15 | L-1011-385-3
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Superseded AD: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Superseded By: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: 76-17-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2704

AD NUMBER:   76-17-05

SUBJECT HEADING:   LOCKHEED-CALIFORNIA Model L-1011-385 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 2, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-17-05 LOCKHEED-CALIFORNIA: Amendment 39-2704. Applies to Lockheed L- 1011-385 Series airplanes certificated in all categories.

Compliance required as indicated, unless already accomplished.

To prevent fires which may be ignited by damaged electrical wires, accomplish the following:

(a) Within the next 300 hours time in service after the effective date of this AD.

(1) Inspect the No. 2 generator feeder cables located in the 1519938-103 ECS duct area on the left side of the No. 2 engine S-duct, between FS-1956 and FS-1975, at approximately WL-310, for a minimum clearance of one-half inch between the cables and the closest part of the ECS duct insulated cover in accordance with Lockheed Alert Service Bulletin 093-24-A058, dated June 3, 1976 or later FAA-approved revision.

(2) If the clearance is less than one-half inch, adjust to provide adequate clearance before further flight in accordance with Lockheed Service Bulletin 093-24-A058, dated June 3, 1976 or later FAA-approved revision.

(b) Within the next 300 hours time in service after the effective date of this AD.

(1) Inspect the electrical wire bundles just aft of the lower left hand side of FS-1860 bulkhead which are routed adjacent to the APU bleed air duct, for proper clamping and condition of insulation. If insulation damage is found, check closely for wire damage.

(2) If damage to insulation or wires is found, before further flight, repair in accordance with FAA-approved maintenance procedures.

(c) Within the next 300 hours time in service after the effective date of this AD.

(1) Inspect the left hand and right hand horizontal stabilizer servo units by applying 3,000 PSI hydraulic pressure to each hydraulic system and observing for signs of hydraulic fluid misting or spraying type of leakage, or examine left hand and right hand horizontal servo unit transfer tube areas for signs of external leakage immediately after hydraulic systems have been shut down.

(2) If hydraulic leaks are found, before further flight, repair in accordance with FAA-approved maintenance procedures.

(d) It is requested that a written report on the results of the inspections required by paragraphs (b) and (c), either positive or negative, be forwarded to: Chief, Aircraft Engineering Division, Federal Aviation Administration, Western Region, P. O. Box 92007, World Way Postal Center, Los Angeles, CA 90009.

(Reporting approved by the Office of Management and Budget under OMB 04- RO174).

(e) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(f) Special flight permits may be issued per FAR's 21.197 and 21.199, to authorize flights to a base for accomplishment of the inspections required by this AD.

This amendment becomes effective September 2, 1976.

FOOTER: