Airworthiness Directives; McDonnell Douglas Model DC-8-70 and -70F Series Airplanes

[Federal Register Volume 69, Number 58 (Thursday, March 25, 2004)]
[Rules and Regulations]
[Pages 15234-15236]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-6500]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-133-AD; Amendment 39-13532; AD 2004-06-06]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-8-70 and -
70F 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-8-70 and -70F series 
airplanes, that requires repetitive inspections for cracking of the 
lower cargo doorjamb corners, and corrective action if necessary. For 
certain airplanes, this AD provides for optional terminating action for 
certain repetitive inspections. For certain other airplanes, this AD 
requires modification of the lower cargo doorjamb corners. This action 
is necessary to detect and correct cracking in the lower cargo doorjamb 
corners, which could result in rapid decompression of the fuselage and 
consequent reduced structural integrity of the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Effective April 29, 2004.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of April 29, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service

[[Page 15235]]

Management, Dept. C1-L5A (D800-0024). 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: Jon Mowery, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5322; 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-8-70 and -70F series airplanes was published in the Federal Register 
on November 17, 2003 (68 FR 64827). That action proposed to require 
repetitive inspections for cracking of the lower cargo doorjamb 
corners, and corrective action if necessary. For certain airplanes, 
that action proposed to provide for optional terminating action for 
certain repetitive inspections. For certain other airplanes, that 
action proposed to require modification of the lower cargo doorjamb 
corners.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 264 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 244 airplanes of U.S. registry 
will be affected by this AD.
    The pre-modification inspections, if required, will take 
approximately 24 work hours per airplane at an average labor rate of 
$65 per work hour. Based on these figures, the cost impact of these 
actions required by this AD on U.S. operators is estimated to be $1,560 
per airplane, per inspection cycle.
    The modification, if accomplished, will take approximately 520 work 
hours per airplane, at an average labor rate of $65 per work hour. The 
parts will cost approximately $25,000. Based on these figures, the cost 
impact of this action on U.S. operators is estimated to be $58,800 per 
airplane.
    The post-modification inspections will take approximately 40 work 
hours per airplane, at an average labor rate of $65 per work hour. 
Based on these figures, the cost impact of these actions on U.S. 
operators is estimated to be $634,400, or $2,600 per airplane, per 
inspection cycle.
    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

0
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

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-06-06 McDonnell Douglas: Amendment 39-13532. Docket 2001-NM-
133-AD.

    Applicability: Model DC-8-70 and -70F series airplanes, 
certificated in any category, as listed in McDonnell Douglas Service 
Bulletin DC8-53-078, Revision 01, dated January 25, 2001.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracking in the lower cargo doorjamb 
corners, which could result in rapid decompression of the fuselage 
and consequent reduced structural integrity of the airplane, 
accomplish the following:

    Note 1: This AD is related to AD 93-01-15, amendment 39-8469, 
and will affect Principal Structural Elements (PSEs) 53.08.042 and 
53.08.043 of the DC-8 Supplemental Inspection Document (SID), Report 
L26-011, Volume II, Revision 7, dated April 1993.

Group 1 Airplanes: Inspections and Optional Terminating Action

    (a) For airplanes identified as Group 1 in McDonnell Douglas 
Service Bulletin DC8-53-078, Revision 01, dated January 25, 2001:
    (1) Within 2,000 landings or 3 years after the effective date of 
this AD, whichever occurs first, perform applicable inspections for 
cracking of the lower cargo doorjamb corners, in accordance with the 
Accomplishment Instructions of the service bulletin.
    (i) If no crack is detected during any inspection required by 
this paragraph: Repeat the inspections within the intervals 
specified in paragraph 1.E. of the service bulletin.
    (ii) If any crack is detected during any inspection required by 
this paragraph: Repair before further flight in accordance with the 
Accomplishment Instructions of the service bulletin.
    (2) Modification of the lower cargo doorjamb corners in 
accordance with the Accomplishment Instructions of the service 
bulletin terminates the repetitive inspection requirement of 
paragraph (a)(1)(i) of this AD.
    (3) For airplanes repaired or modified in accordance with 
paragraph (a)(1)(ii) or (a)(2) of this AD: Within 17,000 landings 
after the repair or modification, perform an eddy current inspection 
for cracks of the doorjamb corners, in accordance with the 
Accomplishment Instructions of the service bulletin (Drawing 
SN08530001). Repeat the inspection at intervals not to exceed 4,400 
landings.

[[Page 15236]]

Group 2 Airplanes: Modification

    (b) For airplanes identified as Group 2 in McDonnell Douglas 
Service Bulletin DC8-53-078, Revision 01, dated January 25, 2001:
    (1) Within 2,000 landings or 3 years after the effective date of 
this AD, whichever occurs first, modify the lower cargo doorjamb 
corners in accordance with the Accomplishment Instructions of the 
service bulletin.
    (2) Within 17,000 landings after the modification required by 
paragraph (b)(1) of this AD, perform applicable inspections for 
cracking of the doorjamb corners, in accordance with the 
Accomplishment Instructions of the service bulletin. Repeat the 
inspections at intervals not to exceed 4,400 landings.

Group 3 and Group 4 Airplanes: Inspections

    (c) For airplanes identified as Group 3 and Group 4 in McDonnell 
Douglas Service Bulletin DC8-53-078, Revision 01, dated January 25, 
2001: Within 17,000 landings following accomplishment of the 
modification specified in the service bulletin, perform applicable 
inspections for cracking of the lower cargo doorjamb corners, in 
accordance with the Accomplishment Instructions of the service 
bulletin. Repeat the inspections at intervals not to exceed 4,400 
landings.

All Airplanes: Repair Following Post-Modification Inspections

    (d) If any cracking is detected during any inspection required 
by paragraph (a)(3), (b)(2), or (c) of this AD: Repair before 
further flight in accordance with a method approved by the Manager, 
Los Angeles Aircraft Certification Office (ACO), FAA; or per data 
meeting the type certification basis of the airplane approved by a 
Boeing Company Designated Engineering Representative (DER) who has 
been authorized by the Manager, Los Angeles ACO, to make such 
findings. For a repair method to be approved, the approval must 
specifically refer to this AD.

Credit for Prior Accomplishment

    (e) Inspections done before the effective date of this AD in 
accordance with McDonnell Douglas Service Bulletin DC8-53-078, dated 
February 6, 1996, are acceptable for compliance with the applicable 
inspections required by this AD.
    (f) Inspections and repairs specified in this AD of areas of 
PSEs 53.08.042 and 53.08.043 are acceptable for compliance with the 
applicable requirements of paragraphs (a), (b), and (c) of AD 93-01-
15. The remaining areas of the affected PSEs must be inspected and 
repaired as applicable, in accordance with AD 93-01-15.

Report

    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD: Submit a report of the findings (both positive 
and negative) of each inspection required by this AD to the Manager, 
Los Angeles ACO. Under the provisions of the Paperwork Reduction Act 
of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and 
Budget (OMB) has approved the information collection requirements 
contained in this AD and has assigned OMB Control Number 2120-0056.
    (1) For an inspection done after the effective date of this AD: 
Submit the report within 10 days after the inspection.
    (2) For an inspection done before the effective date of this AD: 
Submit the report within 10 days after the effective date of this 
AD.

Alternative Methods of Compliance

    (h)(1) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
ACO, FAA, is authorized to approve alternative methods of compliance 
(AMOCs) for this AD.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by a 
Boeing DER who has been authorized by the Manager, Los Angeles ACO, 
to make such findings.

Incorporation by Reference

    (i) Unless otherwise specified in this AD, the actions shall be 
done in accordance with McDonnell Douglas Service Bulletin DC8-53-
078, Revision 01, dated January 25, 2001. 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 Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024). 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 April 29, 2004.

    Issued in Renton, Washington, on March 12, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-6500 Filed 3-24-04; 8:45 am]
BILLING CODE 4910-13-P

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