Airworthiness Directives; Boeing Model 707 and 720 Series Airplanes

[Federal Register Volume 65, Number 233 (Monday, December 4, 2000)]
[Rules and Regulations]
[Pages 75588-75589]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-30397]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-378-AD; Amendment 39-12027; AD 2000-24-20]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 707 and 720 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 all Boeing Model 707 and 720 series airplanes, that 
requires repetitive inspections of certain stringers and around certain 
fastener holes of the lower skin of the wings to detect fatigue 
cracking, and repair, if necessary. This action is necessary to detect 
and correct such cracking and consequent damage to adjacent structure, 
which could result in reduced structural integrity of the airplane. 
This action is intended to address the identified unsafe condition.

DATES: Effective January 8, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 8, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. 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 Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: James Rehrl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2783; fax (425) 227-1181.

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 all Boeing Model 707 and 720 
series airplanes was published in the Federal Register on August 10, 
2000 (65 FR 48941). That action proposed to require repetitive 
inspections of certain stringers and around certain fastener holes of 
the lower skin of the wings to detect fatigue cracking, and repair, if 
necessary.

Comment Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter, Boeing, requests that all references to Model 720 
series airplanes be deleted from the proposed rule. Specifically, 
Boeing suggests that:
    <bullet> the Cost Impact paragraph be revised to specify that there 
are approximately ``* * * 49 affected Model 707 series airplanes 
worldwide * * *;''
    <bullet> paragraph (a) of the proposed rule be removed; and
    <bullet> Note 2 of the proposed rule be revised to state that the 
actions required by AD 81-11-06 R1, amendment 39-4178, for Model 720 
airplanes remain in effect. The commenter states that there are no 
Model 720 series airplanes in active service. In addition, the changes 
in Revision 4 of the referenced alert service bulletin affect only 
Model 707 series airplanes.
    The FAA does not concur with the commenter's request to remove 
references to Model 720 series airplanes from this final rule. Even 
though no Model 720 series airplanes are currently in active service, 
including this model in the applicability of the final rule is 
necessary to ensure that the unsafe condition is addressed on any Model 
720 series airplane that is returned to service in the future. In 
addition, the FAA notes that several changes in Revision 4 of the alert 
service bulletin do, in fact, address Model 720 series airplanes. No 
change to this final rule is necessary.

Conclusion

    After careful review of the available data, including the comment 
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 49 Model 707 and 720 series airplanes of 
the affected design in the worldwide fleet. The FAA estimates that 2 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 56 work hours per airplane to accomplish the 
required actions, and that the average labor rate is $60 per work hour. 
Based on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $6,720, or $3,360 per airplane, per inspection cycle.
    The cost impact figure discussed above is 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

[[Page 75589]]

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:

2000-24-20 Boeing: Amendment 39-12027. Docket 99-NM-378-AD.
    Applicability: All Model 707 and 720 series airplanes, 
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 (e) 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 fatigue cracking of certain stringers, and around 
certain fastener holes of the lower skin of the wings, which could 
result in damage to adjacent structure and consequent reduced 
structural integrity of the airplane, accomplish the following:

Initial and Repetitive Inspections

    (a) For Model 720 series airplanes: Within 500 flight cycles 
after the effective date of this AD, perform an initial high 
frequency eddy current (HFEC) inspection to detect cracking, in 
accordance with Figure 1 of Boeing Alert Service Bulletin A3395, 
Revision 4, dated October 28, 1999.
    (b) For Model 707 series airplanes having fewer than 15,000 
total flight cycles as of the effective date of this AD: Prior to 
the accumulation of 15,000 total flight cycles, or within 150 flight 
cycles after the effective date of this AD, whichever occurs later, 
perform an initial HFEC inspection in accordance with Figure 2; 
steps 1, 2, and 3; of Boeing Alert Service Bulletin A3395, Revision 
4, dated October 28, 1999. Repeat the inspection thereafter at 
intervals not to exceed 1,300 flight cycles. Accomplishment of the 
repetitive HFEC inspections terminates the low frequency eddy 
current inspections specified in AD 81-11-06 R1, amendment 39-4178.
    (c) For Model 707 series airplanes having 15,000 total flight 
cycles or more as of the effective date of this AD: Within 150 
flight cycles after the effective date of this AD, perform an 
initial HFEC inspection in accordance with Figure 2; steps 4, 5, and 
6; of Boeing Alert Service Bulletin A3395, Revision 4, dated October 
28, 1999, and accomplish the requirements in paragraphs (c)(1) and 
(c)(2) of this AD.
    (1) Repeat the inspection thereafter at intervals not to exceed 
150 flight cycles until accomplishment of the inspections required 
by paragraph (c)(2) of this AD.
    (2) Within 400 flight cycles after accomplishment of the initial 
inspection required by paragraph (c) of this AD, accomplish the HFEC 
inspections required by paragraph (b) of this AD. Accomplishment of 
these inspections terminates the repetitive inspections required by 
paragraph (c)(1) of this AD.

    Note 2: The actions required by AD 81-11-06 R1, amendment 39-
4178 [with the exception of the LFEC inspections, as specified in 
paragraph (b) of this AD] remain in effect.

Inspect and Repair

    (d) If any cracking is detected during any inspection required 
by this AD, prior to further flight, perform an internal inspection 
in accordance with the Work Instructions specified in Boeing Alert 
Service Bulletin A3395, Revision 4, dated October 28, 1999; and, 
prior to further flight, repair in accordance with a method approved 
by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or 
in accordance with data meeting the type certification basis of the 
airplane approved by a Boeing Company Designated Engineering 
Representative who has been authorized by the Manager, Seattle ACO, 
to make such findings. For a repair method to be approved by the 
Manager, Seattle ACO, as required by this paragraph, the Manager's 
approval letter must specifically reference this AD.

Alternative Methods of Compliance

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

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permit

    (f) 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

    (g) Except as required by paragraph (d) of this AD, the actions 
shall be done in accordance with Boeing Alert Service Bulletin 
A3395, Revision 4, dated October 28, 1999. 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 Airplane Group, P.O. Box 3707, 
Seattle, Washington 98124-2207. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on January 8, 2001.


    Issued in Renton, Washington, on November 22, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-30397 Filed 12-1-00; 8:45 am]
BILLING CODE 4910-13-P

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