AD 64-08-01

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AD Number:
64-08-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS All Models DC-8 and DC-8F Series Aircraft
Subject:
Pitot And Static Line Fittings
Status:
Current
Citation:
(Federal Register: April 2, 1964)
Citation Publish Date:
04/02/1964
Effective Date:
04/02/1964
Make:
The Boeing Company
Model:
DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...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Superseded AD: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Superseded By: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: 64-08-01
CITATION:   [Federal Register: April 2, 1964]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   64-08-01

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS All Models DC-8 and DC-8F Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective April 2, 1964.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
64-08-01 DOUGLAS: Amdt. 710 Part 507 Federal Register April 2, 1964. Applies to All Models DC-8 and DC-8F Series Aircraft.

Compliance required as indicated.

It has been found that excessive torquing of pilot and static line fittings of the pitch trim compensator and the use of a nonreinforced hose can result in the twisting or bending of the pitot and/or static lines and the possible loss of required instruments. To correct this condition, accomplish either (a) or (b) as follows:

(a) Within 300 hours time in service after the effective date of this AD, modify the pitch trim compensator system in accordance with the provisions of paragraph (c).

(b) Accomplish the provisions specified in (1), (2) and (3) and in addition, within 1,500 hours' time in service after the effective date of this AD modify the pitch trim compensator in accordance with the provisions of paragraph (c).

(1) Within 300 hours time in service after the effective date of this AD, unless already accomplished, visually inspect all aircraft for any evidence of bending or twisting of the pitot and static lines associated with the pitch trim compensator in accordance with the Douglas "Pitot Static System Inspection-DC-8" Service Letter CL-78-1966/DEG8-34-15-0 dated November 15, 1963.

(2) Replace any damaged lines before further flight.

(3) Each time the pitot and static line fittings associated with the pitch trim compensator are removed, loosened or retightened, visually inspect the pitot-static lines associated with the pitch trim compensator for any evidence of bending or twisting in accordance with the Douglas "Pitot Static System Inspection - DC-8" Service Letter CL-78-1966/DEG 8-34-15-0 dated November 15, 1963.

(c) Modify the pitch trim compensator system by replacing the pitot and static lines with reinforced lines and securing the pitot and static line fittings in accordance with paragraph 2, Accomplishment Instructions of the Douglas DC-8 Service Bulletin No. 34-51 dated January 9, 1964, or an FAA Western Region, Engineering and Manufacturing Branch approved equivalent.

(Douglas DC-8 Service Bulletin No. 34-51 dated January 9, 1964, and Douglas DC-8 Service Letter CL-78-1966/DEG 8-34-15-0 dated November 15, 1963, pertain to this AD.)

This directive effective April 2, 1964.

FOOTER: