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Airworthiness Directives; McDonnell Douglas Model DC-8 Series Airplanes

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Information about this document as published in the Federal Register.

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AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule; correction.

SUMMARY:

This document corrects and clarifies information in an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model DC-8 series airplanes. That AD currently requires a revision to the Airplane Flight Manual Supplement to ensure that the main deck cargo door is closed, latched, and locked; repetitive inspections of the wire bundle and door latch rollers to detect damage; and repair or replacement of damaged components. That AD also requires, among other actions, modification of the indication and hydraulic systems of the main deck cargo door, and installation of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. This document corrects two errors that resulted in the incorrect references of two paragraphs. This correction is necessary to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of the door, flight control, or severe structural damage.

DATES:

Effective June 7, 2000.

The incorporation by reference of National Aircraft Service, Inc. (NASI) Service Bulletin SB-99-01, Revision A, dated October 15, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 7, 2000 (65 FR 25627, May 3, 2000).

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FOR FURTHER INFORMATION CONTACT:

Michael E. O'Neil, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5320; fax (562) 627-5210.

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SUPPLEMENTARY INFORMATION:

On April 24, 2000, the Federal Aviation Administration (FAA) issued AD 2000-09-01, amendment 39-11709 (65 FR 25627, May 3, 2000), which applies to certain McDonnell Douglas Model DC-8 series airplanes. That AD supersedes AD 93-20-02, amendment 39-8709 (58 FR 53635, October 18, 1993) to continue to require a revision to the Airplane Flight Manual Supplement to ensure that the main deck cargo door is closed, latched, and locked; repetitive inspections of the wire bundle and door latch rollers to detect damage; and repair or replacement of damaged components. That AD also requires, among other actions, modification of the indication and hydraulic systems of the main deck cargo door, and installation of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. That AD was prompted by the FAA's determination that certain main deck cargo door systems do not provide an adequate level of safety; the latching and locking mechanisms are not of adequate design to prevent structural deformation in the event of component jamming; and that there is an absence of a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked. The actions required by that AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of the door, flight control, or severe structural damage.

Need for the Correction

Since the issuance of AD 2000-09-01, the FAA has reviewed the wording of paragraphs (a), (b), (g)(2), and (g)(3) of the AD and finds that clarification is necessary. Paragraph (a) of AD 93-20-02 was redesignated as paragraph (b) in AD 2000-09-01. Paragraph (b) of AD 93-20-02 was redesignated as paragraph (a) in AD 2000-09-01. The FAA's intent in paragraph (g)(2) of AD 2000-09-01 was that alternative methods of compliance (AMOC) approved previously to paragraph (a) of AD 93-20-02, are approved as AMOC's with only paragraph (b) of this AD, NOT paragraph (a). In addition, AMOC's approved previously to paragraph (b) of AD 93-20-02, are approved as AMOC's with only paragraph (a) of this AD, NOT paragraph (b). Therefore, this action revises paragraphs (g)(2) and (g)(3) of this AD to correct certain paragraph designations.

Correction of Publication

This document corrects and clarifies the errors and correctly adds the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13).

The AD is reprinted in its entirety for the convenience of affected operators. The effective date of the AD remains June 7, 2000.

Since this action only clarifies and corrects certain paragraph designations, it has no adverse economic impact and imposes no additional burden on any person. Therefore, the FAA has determined that notice and public procedures are unnecessary.

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List of Subjects in 14 CFR Part 39

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Adoption of the Correction

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Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (

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PART 39—AIRWORTHINESS DIRECTIVES

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1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

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[Corrected]

2. Section 39.13 is amended by correctly adding the following airworthiness directive (AD):

2000-09-01 R1 McDonnell Douglas: Amendment 39-11809. Docket 99-NM-338-AD.

Applicability: Model DC-8 series airplanes that have been converted from a passenger to a cargo-carrying (“freighter”) configuration in accordance with Supplemental Type Certificate (STC) SA1802SO or SA421NW; certificated in any category.

Note 1:

This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (g)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of the door, flight control, or severe structural damage, accomplish the following:

Restatement of Requirements of AD 93-20-02

Actions Addressing the Main Deck Cargo Door

(a) Within 7 days after January 21, 1992 (the effective date of AD 92-02-05, amendment 39-8141), and thereafter at intervals not to exceed 100 hours time-in-service, perform the following inspections:

(1) Inspect the cargo door wire bundle between the exit point of the cargo liner and the attachment point on the cargo door to detect crimped, frayed, or chafed wires; and inspect for damaged, loose, or missing hardware mounting components. Prior to further flight, repair any damaged wiring or hardware mounting components in accordance with FAA-approved maintenance procedures.

(2) Inspect the cargo door latch rollers in the lower sill of the cargo door opening of the airplane to ensure that all twelve rollers can be freely rotated by hand. Prior to further flight, replace any discrepant roller components found, and repair any rollers that cannot be rotated freely by hand, in accordance with FAA-approved maintenance procedures.

(b) Within 7 days after November 17, 1993 (the effective date of AD 93-20-02, amendment 39-8709), revise the Limitations Section of the appropriate FAA-approved Airplane Flight Manual Supplement (AFMS) by replacing item 5 in the AFMS for SA1802SO, and item 6 in the AFMS for SA421NW, with the following. (This may be accomplished by inserting a copy of this AD into the AFMS.)

“Prior to initiating the cargo door closing sequence, a flight crew member must verify that the cargo door warning light is illuminated. After the door closing sequence is complete, and visual verification has been made that the latches are closed and the lockpins are properly engaged, a flight crew member must verify that the cargo door warning light is extinguished, and then conduct a PRESS-TO-TEST of the warning light to ensure that the light is operational. Pull the cargo door circuit breakers labeled ‘pump’ and ‘valve’ prior to takeoff. Methods for documentation of compliance with the preceding procedures must be approved by the FAA Principal Maintenance Inspector (PMI).”

New Requirements of This AD

Actions Addressing the Main Deck Cargo Door Powered Lock Systems

(c) Except as provided by paragraph (f) of this AD, within 30 days after the effective date of this AD, unless previously Start Printed Page 41871accomplished within the last 18 months prior to the effective date of this AD, replace the circuit breakers of the main deck cargo door labeled “pump” and “valve” with new circuit breakers.

Actions Addressing the Main Deck Cargo Door Hydraulic Systems

(d) Within 18 months after the effective date of this AD, modify the mechanical and hydraulic systems of the main deck cargo door, in accordance with National Aircraft Service, Inc. (NASI) Service Bulletin SB-99-01, Revision A, dated October 15, 1999.

Actions Addressing the Main Deck Cargo Door Indication System

(e) Within 18 months after the effective date of this AD, modify the indication system of the main deck cargo door to indicate to the pilots whether the main deck cargo door is closed, latched, and locked; install a means to visually inspect the locking mechanism of the main deck cargo door; install a means to remove power to the door while the airplane is in flight; and install a means to prevent pressurization to an unsafe level if the main deck cargo door is not closed, latched, and locked; in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.

Note 2:

Installation of NASI Vent Door System STC ST01116CH, is an approved means of compliance with the requirements of paragraph (e) of this AD.

(f) Compliance with both paragraphs (d) and (e) of this AD constitutes terminating action for the requirements of both paragraphs (a) and (b) of this AD, and the AFMS revision required by paragraph (b) of this AD may be removed. Compliance with paragraph (e) of this AD within 30 days after the effective date of this AD eliminates the requirement to comply with paragraph (c) of this AD.

Alternative Methods of Compliance

(g)(1) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA PMI, who may add comments and then send it to the Manager, Los Angeles ACO.

Note 3:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO.

(2) Alternative methods of compliance to paragraph (a) of AD 93-20-02, amendment 39-8709, approved previously in accordance with that AD, are approved as alternative methods of compliance with only paragraph (b) of this AD.

(3) Alternative methods of compliance to paragraph (b) of AD 93-20-02, amendment 39-8709, approved previously in accordance with that AD, are approved as alternative methods of compliance with only paragraph (a) of this AD.

Special Flight Permits

(h) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

Incorporation by Reference

(i) The modification required by paragraph (d) of this AD shall be done in accordance with National Aircraft Service, Inc. (NASI) Service Bulletin SB-99-01, Revision A, dated October 15, 1999. This incorporation by reference was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of June 7, 2000 (65 FR 25627, May 3, 2000). Copies may be obtained from National Aircraft Service, Inc. (NASI), 9133 Tecumseh-Clinton Road, Tecumseh, MI 49286. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

(j) The effective date of this amendment remains June 7, 2000.

Appendix 1

Excerpt From an FAA Memorandum to Director—Airworthiness and Technical Standards of ATA, Dated March 20, 1992

(1) Indication System:

(a) The indication system must monitor the closed, latched, and locked positions, directly.

(b) The indicator should be amber unless it concerns an outward opening door whose opening during takeoff could present an immediate hazard to the airplane. In that case the indicator must be red and located in plain view in front of the pilots. An aural warning is also advisable. A display on the master caution/warning system is also acceptable as an indicator. For the purpose of complying with this paragraph, an immediate hazard is defined as significant reduction in controllability, structural damage, or impact with other structures, engines, or controls.

(c) Loss of indication or a false indication of a closed, latched, and locked condition must be improbable.

(d) A warning indication must be provided at the door operators station that monitors the door latched and locked conditions directly, unless the operator has a visual indication that the door is fully closed and locked. For example, a vent door that monitors the door locks and can be seen from the operators station would meet this requirement.

(2) Means to Visually Inspect the Locking Mechanism:

There must be a visual means of directly inspecting the locks. Where all locks are tied to a common lock shaft, a means of inspecting the locks at each end may be sufficient to meet this requirement provided no failure condition in the lock shaft would go undetected when viewing the end locks. Viewing latches may be used as an alternate to viewing locks on some installations where there are other compensating features.

(3) Means to Prevent Pressurization:

All doors must have provisions to prevent initiation of pressurization of the airplane to an unsafe level, if the door is not fully closed, latched and locked.

(4) Lock Strength:

Locks must be designed to withstand the maximum output power of the actuators and maximum expected manual operating forces treated as a limit load. Under these conditions, the door must remain closed, latched and locked.

(5) Power Availability:

All power to the door must be removed in flight and it must not be possible for the flight crew to restore power to the door while in flight.

(6) Powered Lock Systems:

For doors that have powered lock systems, it must be shown by safety analysis that inadvertent opening of the door after it is fully closed, latched and locked, is extremely improbable.

Start Signature

Issued in Renton, Washington, on June 28, 2000.

Ali Bahrami,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

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[FR Doc. 00-16926 Filed 7-6-00; 8:45 am]

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