AD 76-03-03

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AD Number:
76-03-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F and DC-10-40 Airplanes
Subject:
Spoiler Control Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/17/1976
Make:
The Boeing Company
Model:
DC-10-10 | DC-10-10F | DC-10-30 | DC-10-30F (KC-10A, KDC-10) | DC-10-40
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 76-03-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2509

AD NUMBER:   76-03-03

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, DC-10-10F, DC-10-30, DC-10-30F and DC-10-40 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 17, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-03-03 MCDONNELL DOUGLAS: Amendment 39-2509. Applies to Models DC-10-10, DC-10-10F, DC-10-30, DC-10-30F and DC-10-40 airplanes, certificated in all categories.

Compliance required as indicated.

To prevent possible jamming of the spoiler handle subsequent to ground spoiler deployment, accomplish the following:

PART I. On those airplanes which incorporate a spoiler control assembly P/N ABH 7220-505 or ABH 7220-507 that has not been modified in accordance with McDonnell Douglas DC-10 Service Bulletin No. 27-119, dated May 29, 1975, or later FAA-approved revisions:

(a) Within 300 hours' additional time in service after the effective date of this AD, unless already accomplished, either

(1) Deactivate the autospoilers and placard them inoperative per McDonnell Douglas AOL 10-108, Revision "C", or later FAA-approved revisions; or

(2) Perform the functional check described in paragraph (3), below, and the corrective action set forth at paragraph (4), below, as necessary.

(3) The functional check is to determine if a condition exists where the spoiler handle cannot be disarmed and retracted subsequent to automatic ground spoiler deployment. The check is to be performed while the aircraft is on the ground. All three hydraulic systems must be pressurized for this check, and the flaps must be positioned to 25 degrees or less.

(i) Place all 3 throttle levers at the idle position. Place the spoiler/speedbrake lever at the retract position, and lift up to arm the spoiler/speedbrake lever,

(ii) Lift number 1 and 3 engine reverse levers to the reverse thrust position. Observe that the spoiler/speedbrake lever is driven aft and latches in the ground spoiler detent.

(iii) Advance number 2 engine throttle lever to at least 2 1/2 inches forward of the idle stop. Observe that the spoiler/speedbrake lever drops downward to unlatch from the ground spoiler detent and retracts completely and disarms as a result of number 2 engine throttle advancement.

(4) If the spoiler/speedbrake lever does not react as indicated in the functional check specified in paragraph (3), prior to further flight either deactivate and placard the auto-spoilers inoperative per McDonnell Douglas AOL 10-108, Revision "C", or later FAA-approved revision or modify the speedbrake module assembly, as applicable, in accordance with McDonnell Douglas DC-10 Service Bulletin No. 27-52, dated May 23, 1973, and McDonnell Douglas DC-10 Service Bulletin No. 27-51, Revision 1, dated September 23, 1975, or later FAA-approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(b) After the effective date of this AD, each time the unmodified speedbrake module assembly undergoes maintenance, prior to further flight conduct the functional check specified in paragraph (a).

(c) After the effective date of this AD, prior to installation on an airplane, a spare speedbrake module assembly must be modified, as applicable, in accordance with McDonnell Douglas DC-10 Service Bulletin No. 27-52, dated May 23, 1973, and McDonnell Douglas DC-10 Service Bulletin No. 27-51, Revision 1, dated September 23, 1975, or later FAA-approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region.

PART II. On all airplanes:

(a) Within the next 4000 hours' additional time in service after the effective date of this AD, unless already accomplished, identify and remove speedbrake module assembly P/N ABH 7178-505, ABH 7178-509 or ABH 7178-511, if installed, and replace with P/N ABH 7178-517, ABH 7178-519, ABH 7178-521, ABH 7178-523, or other part approved by the Chief, Aircraft Engineering Division, FAA Western Region. Following accomplishment of this action, the specified functional check requirements of paragraph (a)(3) in Part I of this AD may be discontinued. Thereafter normal maintenance procedures are to be followed.

Special flight permits may be issued under FAR 21.197 and 21.199 for the purpose of operating the aircraft to a base to perform the requirements of this AD.

This amendment becomes effective February 17, 1976.


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