AD 89-17-01 R1

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AD Number:
89-17-01 R1
Document Type:
AD Final Rules
Docket Number:
89-NM-183-AD
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8F-54, -55, DC-8-61F, -62F, -63F, -71F, -72F, and -73...Show more
Subject:
Main Cargo Door
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/13/1990
Make:
The Boeing Company
Model:
DC-8-33 | DC-8-43 | DC-8-61F | DC-8-62F | DC-8-63F | DC-8-71F | DC-8-72F | DC-8-73F | DC-8F-54 | DC-8F-55
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Superseded AD: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Superseded By: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: 89-17-01 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   89-NM-183-AD

AMENDMENT:   39-6521

AD NUMBER:   89-17-01 R1

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8F-54, -55, DC-8-61F, -62F, -63F, -71F, -72F, and -73F Series Airplanes and DC-8-33 and DC-8-43 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 13, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
89-17-01 R1 MCDONNELL DOUGLAS: Amendment 39-6285 as revised by Amendment 39-6521. Docket No. 89-NM-183-AD.

Applicability: Model DC-8F-54, -55, DC-8-61F, -62F, -63F, -71F, -72F, and -73F series airplanes, as listed in McDonnell Douglas DC-8 Service Bulletins 52-71, dated September 12, 1969; 52-74, Revision 2, dated November 19, 1975; 52-75, dated August 9, 1974; 52-76, Revision 3, dated January 29, 1986; 52-80, dated March 23, 1977; certificated in any category. Also applies to Model DC-8-33 airplanes with STC Number SA3403WE incorporated, and Model DC-8-43 airplanes with STC Number SA3749WE incorporated, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent inadvertent opening of the main cargo door in flight, a condition which could result in loss of pressurization and control of the aircraft, accomplish the following:

A. Within 14 days after August 18, 1989 (the effective date of Amendment 39-6285), ensure that the main cargo door is closed, latched, and locked prior to takeoff following each operation of the door, in accordance with the procedures specified below. The procedures required by this paragraph must be accomplished by qualified and trained personnel, and the training program must be approved by the FAA Principal Maintenance Inspector (PMI). The method for documentation of compliance must also be approved by the FAA PMI.

1. From the outside of the airplane perform a visual check of the exterior manual latch controls, to ensure that the latch actuating shaft and the lock pin handle are in the LOCK position; or

2. Perform a visual check of the latches and lock pins, located on the inside of the main cargo door, to ensure that the latches are in the closed position and the lock pins are in the locked position.

3. Prior to taxi, communicate to the flight crew that the main cargo door has been closed, latched, locked, and checked.

B. Unless the modifications described in paragraph F. of this AD have previously been accomplished, within the next 30 days after August 18, 1989 (the effective date of Amendment 39-6285), and thereafter at intervals not to exceed 45 days, conduct a main cargo door-open indicating system functional check in accordance with McDonnell Douglas All Operator's Letter (AOL) 8-669, dated April 19, 1974, paragraph 1. If the main cargo door-open indicating system functional check is not successfully accomplished, repair the main cargo door-open indicating system prior to further flight, in accordance with AOL 8-669.

C. For airplanes with a hydraulic cargo door latch system, accomplish the following:

1. Within 30 days after August 18, 1989 (the effective date of Amendment 39-6285), and thereafter at intervals not to exceed 45 days, inspect and modify the main cargo door control panel access door plate and "T" handle stowage clip in accordance with McDonnell Douglas AOL 8-669, dated April 19, 1974, paragraph 2. In addition, inspect the control panel access door to ensure the door can be secured in the down and locked position. If the control panel access door can not be secured in the down and locked position, repair prior to further flight.

2. Unless previously accomplished in accordance with paragraph (2) of AD 75-03-02, Amendment 39-2075, within 30 days after August 18, 1989 (the effective date of Amendment 39-6285), verify that the main cargo door hydraulic control valve shaft operates freely, without binding, between the operate neutral and neutral lock positions. This shall be accomplished by opening the main cargo door hydraulic control valve control panel access door; raising the "T" handle Douglas P/N 4777888-1, and pulling the "T" handle vertically upward to its maximum travel (operate neutral position). When the vertical force on the "T" handle is relieved, the main cargo door hydraulic control valve shaft should return to the neutral lock (down) position without binding. Replace the main cargo door hydraulic control valve, Douglas P/N 5777869-5001 or 5919985-5001, prior to further flight, if the valve shaft does not return freely to the neutral lock position.

D. Within 30 days after August 18, 1989 (the effective date of Amendment 39-6285), inspect the main cargo door exterior lock pin handle and latch actuating shaft markings in accordance with McDonnell Douglas AOL 8-669, dated April 19, 1974, paragraph 7, and with one of the following McDonnell Douglas Drawings: 7718621-59 and -61, Revision "AV"; or 5633828, Revision "E"; or 5633939, Revision "C"; or 5804421, Revision "A/H". If the exterior markings are not correct, mark in accordance with any of the above McDonnell Douglas drawings prior to further flight.

E. Except for airplanes with an independent or self-supporting main cargo door hydraulic system, within one year after the effective date of this amendment install a main cargo door hydraulic isolation valve in accordance with McDonnell Douglas Service Bulletin 52-74, Revision 2, dated November 19, 1975.

F. Within one year after the effective date of this amendment install a new main cargo door-open indicating circuit, revise the existing main cargo door-open indicating circuit, and install a main cargo door-open indicating system test circuit, in accordance with McDonnell Douglas Service Bulletin 52-76, Revision 3, dated January 29, 1986. Compliance with the requirements of paragraph B., above, may be terminated upon the accomplishment of the requirements of this paragraph.

G. Within the next 18 months after the effective date of this amendment, accomplish the following:

1. Install a main cargo door lock mechanism view window in accordance with McDonnell Douglas Service Bulletin 52-75, dated August 9, 1974; and

2. Install a main cargo door vent system in accordance with McDonnell Douglas Service Bulletin 52-80, dated March 23, 1977; and

3. Modify the main cargo door latch operating mechanism in accordance with McDonnell Douglas Service Bulletins 52-71 dated September 12, 1969; and

4. Install a main cargo door hinge pin retainer on each end of the hinge, in a manner approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, that will retain the hinge pin in the event of a structural failure of the pin; and

5. Install a vent door-open indicating system, in a manner approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, that will signal the appropriate flight crew member when the main cargo door vent door is not fully closed and latched.

H. Compliance with the requirements of paragraphs E., F., G.1., G.2., G.3., and G.5., constitute terminating action for the initial and repetitive inspections required by paragraphs A., B., and C.1. of this AD.

I. The checks and modifications specified in paragraphs A. through G. of this AD are not required on airplanes which have the main cargo door deactivated and secured in the closed and locked position, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, until that door is reactivated.

J. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office.

K. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California, Attention: Business Unit Manger, Technical Publications, C1-HCW (54-60). This information may be examined at FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California.

Airworthiness Directive 89-17-01 superseded AD 75-03-02 (Amendment 39-2075) and AD 84-23-02 (Amendment 39-4953).

This AD revises AD 89-17-01, amendment 39-6285.

This amendment (39-6521, AD 89-17-01 R1) becomes effective on April 13, 1990.


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