AD 78-01-15

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AD Number:
78-01-15
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes
Subject:
Elevator Geared Crank Arms
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/01/1978
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Superseded AD: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Superseded By: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: 78-01-15
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3198

AD NUMBER:   78-01-15

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 1, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-01-15 MCDONNELL DOUGLAS: Amendment 39-3118 as amended by Amendment 39-3198. Applies to Model DC-8 Series airplanes, certificated in all categories.

Compliance required as indicated.

To prevent failure of the elevator geared tab crank arms and to provide a means of detecting jamming of the elevator surface, comply with the following:

(a) Within the next 12 months after the effective date of this AD, unless already accomplished, increase the elevator geared tab crank assembly clearance by modifying the elevator leading edge cutouts and covers, and modify and reidentify the elevator geared tab links, modify rod ends as required, and chamfer the horizontal stabilizer box fittings in accordance with McDonnell Douglas DC-8 Service Bulletin 27-262 dated July 15, 1977 or later FAA approved revisions.

NOTE: Compliance with the following requirements of Service Bulletin 27-262 is optional:

(i) The installation of steel geared-tab links to replace the existing links.

3802767-1 (new) for 4710541

3802768-1 (new) for 4710542

(ii) The provision of additional clearance between the elevator hinge support fitting Part No. 3619433 and the elevator leading edge spar (view D-D, page 8 of DC-8 Service Bulletin 27-262).

(b) Within the next 18 months after the effective date of this AD, unless already accomplished, install an elevator position indicator system in accordance with McDonnell Douglas DC-8 Service Bulletin 27-254 dated March 5, 1975 or later FAA approved revision.

(c) Equivalent modifications or operational procedures may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(d) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base for the accomplishment of the modifications required by this AD.

(e) Aircraft which have been modified in accordance with Paragraph (b) may be operated with the elevator position indicator system inoperative provided:

(i) Prior to each takeoff verify proper elevator operation by a ground observer, and by utilizing the elevator flight control check procedure of McDonnell Douglas DC-8 Alert Service Bulletin A27-264 dated May 14, 1977 or later FAA approved revision.

(ii) The aircraft is not dispatched from a station where repairs or replacements on the elevator position indicator system can be made.

(f) Within 30 days after the effective date of this AD as amended, unless already accomplished, and until Paragraph (b) of this AD is accomplished, either:

(i) Install the following placard in full view of both pilots

PRIOR TO EACH TAKEOFF, PERFORM AN ELEVATOR CONTROL
SYSTEM CHECK IN ACCORDANCE WITH DC-8 SERVICE
BULLETIN A27-264.

(ii) or, include an instruction in the DC-8 Operations Manual and a check list item which specifies those control checks identified in SB A27-264.

Amendment 39-3118 became effective February 13, 1978.

This Amendment 39-3198 becomes effective June 1, 1978.


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