[Federal Register Volume 64, Number 207 (Wednesday, October 27, 1999)]
[Proposed Rules]
[Pages 57806-57807]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-28085]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-309-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
DC-8 series airplanes. This proposal would require detailed visual and 
eddy current inspections of the lower wing skin at the 3 outboard 
fasteners of the stringer 64 end fitting to detect cracks; and 
corrective actions, if necessary. This proposal is prompted by reports 
of fatigue cracks found in the lower wing skin initiating from the 
outboard fasteners of the stringer 64 end fitting. The actions 
specified by the proposed AD are intended to prevent such fatigue 
cracking, which could reduce structural integrity and loss of fail-safe 
capability of the airplane.

DATES: Comments must be received by December 13, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-309-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule 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 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.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 98-NM-309-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 98-NM-309-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of fatigue cracks in the lower wing 
skin at the 3 outboard fasteners of the stringer 64 end fitting. These 
cracks were discovered during inspections conducted as part of the 
Supplemental Inspection Document (SID) program, required by AD 93-01-
15, amendment 39-8469 (58 FR 5576, January 22, 1993). Investigation 
revealed that such cracking was caused by fatigue-related stress. 
Fatigue cracking of the wing skin at the 3 outboard fasteners of the 
stringer 64 end fitting, if not detected in a timely manner, could 
result in reduced structural integrity and loss of fail-safe capability 
of the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Service 
Bulletin DC8-57-100, Revision 01, dated August 26, 1998. The service 
bulletin describes procedures for detailed visual and eddy current 
inspections to detect cracks of the lower wing skin at the 3 outboard 
fasteners of the stringer 64 end fitting; and corrective actions, if 
necessary. The corrective actions involve accomplishing a preventative 
modification (including stress or split sleeve coining of holes, and 
installing new pins), replacing pins with new pins, and repairing, as 
applicable. Accomplishment of the actions specified in the service 
bulletin is intended to adequately address the identified unsafe 
condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletin described previously, except as discussed below.

[[Page 57807]]

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the service bulletin specifies 
that the manufacturer may be contacted for disposition of certain 
repair conditions, this proposal would require the repair of those 
conditions to be accomplished in accordance with a method approved by 
the FAA.
    Operators should also note that the repair procedures for Condition 
2 of the Work Instructions of the service bulletin do not provide for a 
follow-on inspection of the repaired area. The FAA has determined that 
a follow-on inspection of the repaired area is necessary to provide an 
appropriate level of safety.

Cost Impact

    There are approximately 294 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 251 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
4 work hours per airplane to accomplish the proposed inspection, and 
that the average labor rate is $60 per work hour. Based on these 
figures, the cost impact of the inspection proposed by this AD on U.S. 
operators is estimated to be $60,240, or $240 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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, in accordance with Executive Order 12612, it is 
determined that this proposal would not have sufficient federalism 
implications to warrant the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

McDonnell Douglas: Docket 98-NM-309-AD.

    Applicability: Model DC-8 series airplanes, as listed in 
McDonnell Douglas Service Bulletin DC8-57-100, Revision 01, dated 
August 26, 1998; 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 (b) 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 fatigue cracking of the lower wing skin, which could 
reduce structural integrity and loss of fail-safe capability of the 
airplane, accomplish the following:

    Note 2: This AD will affect Principal Structural Elements (PSE) 
57.08.037, 57.08.038, 57.08.021, and 57.08.022 of the DC-8 
Supplemental Inspection Document (SID).

Inspection, Repair, and Modification

    (a) Within 24 months after the effective date of this AD, 
perform detailed visual and eddy current inspections to detect 
cracks in the lower wing skin fastener holes in the area surrounding 
3 outboard fasteners of the stringer 64 end fitting, in accordance 
with McDonnell Douglas Service Bulletin DC8-57-100, Revision 01, 
dated August 26, 1998.

    Note 3: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (1) If any crack is detected in the skin fastener holes and it 
is less than 3.1 inches long, prior to further flight, repair in 
accordance with the service bulletin. Within 14,100 landings after 
accomplishment of the repair, inspect the lower wing skin to detect 
cracks, in accordance with a method approved by the Manager, Los 
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate.
    (2) If any crack is detected in the skin fastener holes and it 
is greater than or equal to 3.1 inches long, prior to further 
flight, repair in accordance with a method approved by the Manager 
Los Angeles ACO.
    (3) If no crack is found, within 24 months after the effective 
date of this AD, accomplish the preventative modification (including 
stress or split sleeve coining the three fastener holes in the skin, 
and installing new pins), in accordance with the service bulletin. 
Accomplishment of this action constitutes terminating action for the 
requirements of this AD.

    Note 4: This AD does not terminate the inspection requirements 
for PSE's 57.08.037, 57.08.038, 57.08.021, and 57.08.022 of the DC-8 
SID in accordance with AD 93-01-15, amendment 39-6330.

Alternative Methods of Compliance

    (b) 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, FAA, Transport 
Airplane Directorate. 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 5: 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

    (c) 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.

    Issued in Renton, Washington, on October 21, 1999.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-28085 Filed 10-26-99; 8:45 am]
BILLING CODE 4910-13-P