AD 75-06-07

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AD Number:
75-06-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-10-10, -30, -30F, and -40 Series Airplanes
Subject:
Forward Passenger Doors
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/06/1978
Make:
The Boeing Company
Model:
DC-10-10 | 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Superseded AD: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Superseded By: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: 75-06-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3227

AD NUMBER:   75-06-07

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

ACTION:  

SUMMARY:  

DATES:   Effective July 6, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
75-06-07 MCDONNELL DOUGLAS: Amendment 39-2126 as amended by Amendment 39-2605 is further amended by Amendment 39-3227. Applies to Douglas Model DC-10-10, -30, -30F, and -40 series airplanes, certificated in all categories, with factory serial numbers as indicated in Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions.

To insure proper functioning of forward passenger doors during emergency operation, accomplish the following:

(a) Compliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished.

(1) Inspect the forward passenger door (L & R) operating mechanisms for proper rigging, broken, damaged, or corroded cables, and adjust rigging or replace cables as required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions.

(2) After accomplishment of the inspection per paragraph (a)(1) above, check pneumatic operation of doors (L & R) from both the inside and outside of the aircraft.

(b) Compliance required on airplanes with 5,000 hours' or more total time in service after the effective date of this AD, unless already accomplished per paragraph (a) above within the last 1500 hours' time in service, and thereafter at intervals not to exceed 2250 hours' time in service from the last inspection.

(1) Reinspect the forward passenger door (L & R) mechanism cables, and replace if required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions.

(2) If cable(s) has been replaced, recheck pneumatic operation of applicable door(s) from both the inside and outside of the aircraft.

(3) The repetitive 2250-hour inspections required by paragraph (b) may be discontinued provided stainless steel cables and swivel clevises are installed in accordance with McDonnell Douglas Service Bulletin No. 52-152, dated February 3, 1976, or later FAA-approved revisions.

(c) Compliance required within the next 5000 hours' time in service after accomplishment of the inspection per paragraph (a) above, and thereafter at intervals not to exceed 5000 hours' time in service from the last inspection.

(1) Reinspect the forward passenger door (L & R) mechanism rigging, and adjust if required, in accordance with Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA-approved revisions.

(2) If rigging has been adjusted, recheck pneumatic operation of applicable door(s) from both the inside and outside of the aircraft.

(3) The repetitive 5000-hour inspections required by paragraph (c) may be discontinued provided any one of the following combination of McDonnell Douglas Service Bulletins, or later FAA-approved revisions, has been accomplished:

(i) S./B 52-118, Revision 1, dated February 14, 1975, (Installation of new cams on control mechanism), S/B 52-140, Revision 4, dated August 29, 1975, (Installation of return springs on reservoir actuator), S/B 52-146, Revision 1, dated November 21, 1975, (Installation of direct drive visible downlock), S/B 52-152, dated February 3, 1976, (Installation of stainless steel cables and swivel clevises);

(ii) S/B 52-118, Revision 1, dated February 14, 1975, S/B 52-146, Revision 1, dated November 21, 1975, S/B 52-152, dated February 3, 1976, and S/B 52-154, Revision 1, dated March 1, 1976, (Installation of new reservoir control assembly)

(iii) S/B 52-140, Revision 4, dated August 29, 1975, S/B 52-150, dated September 9, 1975, (Installation of combination up/downlock assembly). S/B 52-152, dated February 3, 1976; or

(iv) S/B 52-150, dated September 9, 1975, S/B 52-152, dated February 3, 1976, and S/B 52-154, Revision 1, dated March 1, 1976.

(4) The repetitive 5000-hour inspection required by paragraph (c) may be replaced by satisfactory accomplishment, at 6000-hour intervals of both electrical and pneumatic door operational checks at applicable doors per Douglas Service Bulletin No. 52-132, Revision 1, dated February 21, 1975, or later FAA approved revisions, provided that all service bulletins except SB 52-152, required by any one of the combination of service bulletins in paragraph (c)(3) have been accomplished.

(d) The Chief, Aircraft Engineering Division, FAA Western Region, may approve equivalent inspections and modifications upon submittal of substantiating data.

(e) Aircraft may be flown to a base for accomplishment of the maintenance required by this AD per FAR's 21.197 and 21.199.

Amendment 39-2126 became effective April 14, 1975.

Amendment 39-2605 became effective May 17, 1976.

This amendment 39-3227 becomes effective July 6, 1978.


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