AD 62-02-04

AD Final Rules - DRS_62-02-04.html
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AD Number:
62-02-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS DC-8 Aircraft
Subject:
Aileron Tab Lockout Bracket
Status:
Current
Citation:
(Federal Register: January 24, 1962)
Citation Publish Date:
01/24/1962
Effective Date:
01/24/1962
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Superseded AD: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Superseded By: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: 62-02-04
CITATION:   [Federal Register: January 24, 1962]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   62-02-04

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS DC-8 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective January 24, 1962.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
62-02-04 DOUGLAS: Amdt. 392 Part 507 Federal Register January 24, 1962. Applies to DC-8 Aircraft Serial Numbers 45252-45289, 45291-45306, 45376-45393, 45408-45413, 45416-45419, 45421-45431, 45433-45437, 45442-45445, 45526, 45565-45570, 45588-45614, 45616-45628 and 45636-45638.

Compliance required as indicated.

To prevent aileron tab lockout mechanism bracket assembly failure, resulting in partial or complete loss of control force to one aileron, the following shall be accomplished:

(a) At periods prescribed in (b), conduct close visual inspection, using low-power magnifying glass or equivalent means, for evidence of cracking of the left and right side aileron tab lockout bracket assemblies, P/N 4643350. The critical areas to be inspected are shown in Douglas Service Bulletin 27-115, Figure 1, Step 3. Any evidence of cracking shall be verified by dye check or equivalent means, with the tab lockout cylinder disconnected from the bracket assembly, within the next 10 hours' time in service following the detection of such evidence of cracking. Any part found to be cracked shall be replaced prior to further flight with an assembly of the same part number which has been inspected in accordance with the provisions of this paragraph and found to be free of cracks or with assembly P/N 3773970-1.

(b) The initial and repetitive inspections of assemblies, P/N 4643350, shall be conducted at the following times:

(1) On assemblies which have accumulated a total time in service of less than 3,000 hours as of the effective date of this AD: Initial inspection within next 350 hours' time in service, but in no event to exceed 3,100 hours' assembly total time in service; repetitive inspections thereafter at intervals not to exceed 350 hours' time in service except that after the assembly total time in service reaches 3,000 hours the repetitive intervals shall not exceed 100 hours' time in service.

(2) On assemblies which have accumulated a total time in service of 3,000 hours or more as of the effective date of this AD: Initial inspection within next 100 hours' time in service; repetitive inspections thereafter at intervals not to exceed 100 hours' time in service.

(c) When assembly, P/N 3773970-1 is installed in place of P/N 4643350, the repetitive inspections may be discontinued.

(d) When assembly P/N 4643350 is replaced with an assembly of the same part number which has been inspected in accordance with (a) and found to be free of cracks, the replacement part shall be reinspected in accordance with the provisions of (b).

(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.

(Douglas Service Bulletin 27-115, Revision No. 1, dated October 25, 1961, pertains to this same subject.)

This directive effective January 24, 1962.


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