[Federal Register Volume 65, Number 131 (Friday, July 7, 2000)]
[Rules and Regulations]
[Pages 41869-41871]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-16926]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-338-AD; Amendment 39-11809; AD 2000-09-01 R1]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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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).

[[Page 41870]]


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.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec. 39.13  [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

[[Page 41871]]

accomplished 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.

    Issued in Renton, Washington, on June 28, 2000.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-16926 Filed 7-6-00; 8:45 am]
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