AD 2000-20-08

[Federal Register Volume 65, Number 195 (Friday, October 6, 2000)]
[Rules and Regulations]
[Pages 59701-59703]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-25432]



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Rules and Regulations
                                                Federal Register
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Federal Register / Vol. 65, No. 195 / Friday, October 6, 2000 / Rules 
and Regulations

[[Page 59701]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-135-AD; Amendment 39-11919; AD 2000-20-08]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model DC-8 series airplanes, 
that requires, for certain airplanes, inspection(s) to detect cracks of 
the doorjamb corners and follow-on actions. For certain other 
airplanes, this AD requires installation of a preventative 
modification; an inspection to detect cracks at the corners of the 
doorjambs of the passenger and service doors; and follow-on actions. 
This amendment is prompted by reports indicating that fatigue cracks 
were found in the fuselage skin and doublers at the corners of the 
doorjambs of the passenger and service doors. The actions specified by 
this AD are intended to detect and correct such fatigue cracking, which 
could result in rapid decompression of the fuselage and consequent 
reduced structural integrity of the airplane.

DATES: Effective November 13, 2000. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of November 13, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
This information may be examined at the Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, 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.

FOR FURTHER INFORMATION CONTACT: Greg DiLibero, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5231; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
DC-8 series airplanes was published in the Federal Register on November 
4, 1999 (64 FR 60134). For certain airplanes, that action proposed to 
require inspection(s) to detect cracks of the doorjamb corners and 
follow-on actions. For certain other airplanes, that AD also proposed 
to require installation of a preventative modification; an inspection 
to detect cracks at the corners of the doorjambs of the passenger and 
service doors; and follow-on actions.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for Proposed AD

    One commenter supports the proposed AD.

Request to Revise a Certain Compliance Time

    One commenter requests that paragraph (e) of the proposed AD be 
revised to include an inspection threshold that can be scheduled from 
the effective date of this AD. The commenter states that such a 
threshold would accommodate Group 4 airplanes that have unknown cycles 
accumulated since accomplishment of the modification.
    The FAA does not concur. In developing an appropriate compliance 
time for this action, the FAA considered the safety implications and 
normal maintenance schedules for timely accomplishment of the 
inspection. In addition, the compliance time of ``within 17,000 
landings following accomplishment of the modification specified in the 
service bulletin'' is based on a damage tolerance assessment of the 
affected structure. Because the reported cracking was caused by fatigue 
related stress (as discussed in the preamble of the proposed AD), the 
FAA finds that airplanes that have accumulated unknown hours on the 
modification must be inspected at the earliest possible time to ensure 
no cracks have initiated since installation of the modification, which 
may have been accomplished more than 17,000 flight hours ago. In 
consideration of these items, the FAA has determined that 17,000 
landings following accomplishment of the modification specified in the 
service bulletin represents an appropriate interval of time allowable 
wherein the inspection can be accomplished during scheduled maintenance 
intervals for the majority of affected operators, and an acceptable 
level of safety can be maintained. However, under the provisions of 
paragraph (g) of the final rule, the FAA may approve requests for 
adjustments to the compliance time if data are submitted to 
substantiate that such an adjustment would provide an acceptable level 
of safety.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 294 Model DC-8 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 251 
airplanes of U.S. registry will be affected by this AD.
    Should an operator be required to accomplish the inspection(s), it 
will take 48 (Group 1 airplanes) and 74 (all other groups of airplanes) 
work hours per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact

[[Page 59702]]

of the inspection(s) required by this AD on U.S. operators is estimated 
to be $2,880 (Group 1 airplanes) and $4,440 (all other groups of 
airplanes) per airplane, per inspection cycle.
    Should an operator be required or elect to accomplish the 
preventative modification, it will take approximately 1,440 work hours 
per airplane to accomplish, at an average labor rate of $60 per work 
hour. Required parts will cost approximately $2,000 per airplane. Based 
on these figures, the cost impact of the preventative modification by 
this AD on U.S. operators is estimated to be $88,400 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-20-08  McDonnell Douglas: Amendment 39-11919. Docket 98-NM-135-
AD.

    Applicability: Model DC-8 series airplanes, as listed in 
McDonnell Douglas Service Bulletin DC8-53-075, dated August 17, 
1995; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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) 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 detect and correct fatigue cracking in the fuselage skin and 
doublers at the corners of the doorjambs of the passenger and 
service doors, which could result in rapid decompression of the 
fuselage and consequent reduced structural integrity of the 
airplane, accomplish the following:

    Note 2: Where there are differences between the service bulletin 
and the AD, the AD prevails.


    Note 3: The words ``repair'' and ``modify/modification'' in this 
AD and in the referenced service bulletin are used interchangeably.


    Note 4: This AD is related to AD 93-01-15, amendment 39-8469, 
and will affect Principal Structural Elements (PSE) 53.08.038, 
53.08.039, 53.08.040, and 53.08.041 of the DC-8 Supplemental 
Inspection Document (SID), Report L26-011, Volume I, Revision 3, 
dated March 1991.

Group 1 Airplanes: Initial Inspection and Follow-on or Corrective 
Actions

    (a) For airplanes identified as Group 1 in McDonnell Douglas 
Service Bulletin DC8-53-075, dated August 17, 1995: Within 2,000 
landings or 3 years after the effective date of this AD, whichever 
occurs first, perform the applicable inspection(s) to detect cracks 
of the doorjamb corners in accordance with the service bulletin.
    (1) If no crack is detected during any inspection required by 
paragraph (a) of this AD, repeat the applicable inspection(s) 
required by paragraph (a) of this AD thereafter at intervals 
specified for Group 1 airplanes in paragraph 1.E. of the service 
bulletin; or accomplish the preventative modification in accordance 
with the service bulletin. Accomplishment of the preventative 
modification constitutes terminating action for the repetitive 
inspection requirements of this paragraph.
    (2) If any crack is detected during any inspection required by 
paragraph (a) of this AD, prior to further flight, repair in 
accordance with the service bulletin, except as provided by 
paragraph (f) of this AD.

Group 1 Airplanes: Actions Following Accomplishment of Preventative 
Modification or Repair

    (b) Within 17,000 landings following accomplishment of the 
modification/repair required by either paragraph (a)(1) or (a)(2) of 
this AD, perform an inspection to detect cracks of the doorjamb 
corners, in accordance with McDonnell Douglas Service Bulletin DC8-
53-075, dated August 17, 1995.
    (1) If no crack is detected, repeat the inspection thereafter at 
intervals not to exceed 4,400 landings.
    (2) If any crack is detected, prior to further flight, repair in 
accordance with the service bulletin, except as provided by 
paragraph (f) of this AD.

Group 2 Airplanes: Preventative Modification, Inspection(s), and 
Repair, If Necessary

    (c) For airplanes identified as Group 2 in McDonnell Douglas 
Service Bulletin DC8-53-075, dated August 17, 1995: Within 2,000 
landings or 3 years after the effective date of this AD, whichever 
occurs first, accomplish the preventative modification in accordance 
with the service bulletin. Within 17,000 landings following 
accomplishment of the preventative modification, perform an 
inspection to detect cracks of the doorjamb corners, in accordance 
with the service bulletin.
    (1) If no crack is detected during any inspection required by 
paragraph (c) of this AD, repeat the inspection thereafter at 
intervals not to exceed 4,400 landings.
    (2) If any crack is detected during any inspection required by 
paragraph (c) of this AD, prior to further flight, repair it in 
accordance the service bulletin, except as provided by paragraph (f) 
of this AD.

Group 3 Airplanes: Revision of Maintenance or Inspection Program

    (d) For airplanes identified as Group 3 in McDonnell Douglas 
Service Bulletin DC8-53-075, dated August 17, 1995: Within 6 years 
following accomplishment of the permanent repair or within 3 years 
after the effective date of this AD, whichever occurs later, revise 
the FAA-approved maintenance or inspection program to include an

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inspection program for the doorjamb corners identified in the 
service bulletin. The new inspection program shall be approved by 
the Manager, Los Angeles Aircraft Certification Office (ACO), FAA.

    Note 5: Requests for approval of inspection procedures of the 
permanent repairs that are proposed for inclusion in the FAA-
approved maintenance or inspection program, as required by this AD, 
should include a damage tolerance assessment.

Group 4 Airplanes: Inspection(s) and Repair, If Necessary

    (e) For airplanes identified as Group 4 in McDonnell Douglas 
Service Bulletin DC8-53-075, dated August 17, 1995: Within 17,000 
landings following accomplishment of the modification specified in 
the service bulletin, perform an inspection to detect cracks of the 
doorjamb corners, in accordance with the service bulletin.
    (1) If no crack is detected during any inspection required 
paragraph (e) of this AD, repeat the inspection thereafter at 
intervals not to exceed 4,400 landings.
    (2) If any crack is detected during any inspection required by 
paragraph (e) of this AD, prior to further flight, repair in 
accordance with the service bulletin, except as provided by 
paragraph (f) of this AD.

Exception to Procedures Specified in the Referenced Service Bulletin

    (f) Where McDonnell Douglas Service Bulletin DC8-53-075, dated 
August 17, 1995, specifies that the manufacturer may be contacted 
for disposition of certain repair conditions, this AD requires the 
repair of those conditions to be accomplished in accordance with a 
method approved by the Manager, Los Angeles ACO.

Alternative Methods of Compliance

    (g) 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 ACO. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 6: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (h) Special flight permits may be issued in accordance with 
Secs. 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) Except as provided by paragraphs (d) and (f) of this AD, the 
actions shall be done in accordance with McDonnell Douglas Service 
Bulletin DC8-53-075, dated August 17, 1995. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
Copies may be inspected at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 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) This amendment becomes effective on November 13, 2000.

    Issued in Renton, Washington, on September 28, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-25432 Filed 10-5-00; 8:45 am]
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