AD 2000-24-06

[Federal Register Volume 65, Number 233 (Monday, December 4, 2000)]
[Rules and Regulations]
[Pages 75585-75588]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-30398]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-363-AD; Amendment 39-12013; AD 2000-24-06]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 707, 727C, and 727-100C 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 707, 727C, and 727-100C series 
airplanes, that currently requires repetitive inspections to detect 
cracking of the main cargo door skin and frames, and repair, if 
necessary. The existing AD also provides optional terminating 
modifications. This amendment requires follow-on repetitive inspections 
of repaired or modified areas for certain airplanes. This amendment is 
prompted by reports of cracking and/or tearing of the main cargo door 
outer skin and subsequent failure of the door frame. The actions 
specified by this AD are intended to detect and correct such cracking 
and/or tearing, which could result in failure of the door frame and 
consequent rapid decompression of the airplane.

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: Walt Sippel, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2774; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 83-02-09, 
amendment 39-4549 (48 FR 6953, February 17, 1983); which is applicable 
to certain Boeing Model 707, 727C, and 727-100C airplanes; was 
published in the Federal Register on April 19, 2000 (65 FR 20924). The 
action proposed to continue to require repetitive inspections to detect 
cracking of the main cargo door skin and frames, and repair, if 
necessary, and to continue to provide for optional terminating 
modifications. The action also proposed to require new follow-on 
repetitive inspections of repaired or modified areas for certain 
airplanes.

Explanation of Change in the Final Rule

    Paragraph (e)(2) of the proposed rule states that it applies to 
airplanes on which the modification specified in Part II, Option 2 of 
the Accomplishment Instructions of Boeing Service Bulletin 727-52A0079, 
Revision 4, dated June 19, 1981, Revision 5, dated June 17,

[[Page 75586]]

1983, or Revision 6, dated January 11, 1990, has been accomplished. 
However, Part II, Option 2, and the modification contained therein 
(which involves installation of over-sized, protruding-head rivets), 
appears only in Revision 6 of the service bulletin. Therefore, 
paragraph (e)(2) of this final rule has been revised to refer only to 
Revision 6 of the service bulletin. In addition, paragraph (e)(1) of 
this final rule has been revised to clarify that the modification 
referred to as ``Part II, Option 1'' in Revision 6 of the service 
bulletin is referred to as ``Part II'' of Revisions 4 and 5 of the 
service bulletin.

Comments

    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.

Request to Reference Terminating Action

    One commenter requests that the FAA revise the proposed rule to 
terminate the repetitive high frequency eddy current (HFEC) inspections 
specified in paragraph (e) of the proposed AD following installation of 
over-sized, protruding-head rivets in the skin of the main cargo door. 
The commenter points out that such installation of over-sized, 
protruding-head rivets in crack-free holes is one of two options for 
modification in Revision 5 of the service bulletin. The commenter 
states that eliminating the requirement for HFEC inspections would be 
consistent with the requirements of AD 91-06-06, amendment 39-6921 (56 
FR 9612, March 7, 1991), which does not require repetitive HFEC 
inspections of the upper row of fuselage lap splices once protruding-
head rivets have been installed.
    The FAA concurs with the intent of the commenter's request and its 
rationale. However, the FAA infers that, though the commenter refers to 
Revision 5 of the service bulletin, the correct reference should be to 
Revision 6 of the service bulletin. (As noted above, Revision 5 does 
not describe the modification to which the commenter refers.) For 
airplanes modified per Part II, Option 2 of the Accomplishment 
Instructions of the service bulletin, paragraph (e)(2) of the proposed 
rule specifies repetitive internal and external detailed visual and 
HFEC inspections of the modified area. The FAA has determined that the 
HFEC inspection is no longer necessary following accomplishment of the 
modification in Part II, Option 2 of the Accomplishment Instructions of 
Revision 6 of the service bulletin. Therefore, paragraph (e)(2) of this 
final rule has been revised to delete reference to an HFEC inspection.

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 with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 50 Model 707 and 308 Model 727 series 
airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 1 Model 707 and 81 Model 727 airplanes of U.S. registry 
will be affected by this AD.
    The cost impact information in AD 83-02-09 inadvertently contained 
information relevant only to the X-ray inspection; however, since the 
detailed visual and eddy current inspections are also acceptable 
methods to detect cracking, this AD includes the estimated number of 
work hours necessary to accomplish any one of the three inspection 
methods. Additionally, the FAA has recently reviewed the figures it has 
used over the past several years in calculating the economic impact of 
AD activity. In order to account for various inflationary costs in the 
airline industry, the FAA has determined that it is necessary to 
increase the labor rate used in these calculations from $40 per work 
hour to $60 per work hour. The cost impact information, below, has been 
revised to reflect these changes.
    Should an operator elect to accomplish the detailed visual 
inspection that is currently required by AD 83-02-09, it will take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the detailed visual inspection is estimated to be $60 per 
airplane.
    Should an operator elect to accomplish the eddy current inspection 
that is currently required by AD 83-02-09, it will take approximately 1 
work hour per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of the eddy 
current inspection is estimated to be $60 per airplane.
    Should an operator elect to accomplish the X-ray inspection that is 
currently required by AD 83-02-09, it will take approximately 3 work 
hours per airplane to accomplish, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the X-ray 
inspection is estimated to be $180 per airplane.
    The detailed visual inspection (for Model 727 series airplanes 
only) required by this AD will take approximately 1 work hour per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the detailed visual 
inspection is estimated to be $4,860, or $60 per airplane.
    The eddy current inspection (for Model 727 series airplanes only) 
required by this AD will take approximately 1 work hour per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the eddy current inspection is 
estimated to be $4,860, or $60 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.

[[Page 75587]]

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 removing amendment 39-4549 (48 FR 
6953, February 17, 1983), and by adding a new airworthiness directive 
(AD), amendment 39-12013, to read as follows:

2000-24-06 Boeing: Amendment 39-12013. Docket 99-NM-363-AD. 
Supersedes AD 83-02-09, Amendment 39-4549.

    Applicability: Model 707, 727C, and 727-100C series airplanes; 
as listed in Boeing Service Bulletins 2999, Revision 3, dated 
January 12, 1972, and 727-52-79, Revision 4, dated June 19, 1981; 
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)(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 detect and correct cracking of the main cargo door skin and 
frames, which could result in failure of the door frame, and 
consequent rapid decompression of the airplane, accomplish the 
following:

    Note 2: For the purposes of this AD, a detailed visual 
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.''

Restatement of Requirements of AD 83-02-09:

Initial Inspection

    (a) Within 500 landings after March 3, 1983 (the effective date 
of AD 83-02-09, amendment 39-4549), or prior to the accumulation of 
25,000 total landings after March 3, 1983, whichever occurs later: 
Perform an inspection (detailed visual, eddy current, or X-ray) to 
detect cracks of the main cargo door outer skin and frames between 
body stations (BS) 505 and 595, from the lower edge of the door 
hinge a minimum of 6 inches down, and 6 inches above, and 3 inches 
below the center line of stringer 10, in accordance with Boeing 
Service Bulletin 2999, Revision 3, dated January 12, 1972, or 
Revision 4, dated January 31, 1991 (for Model 707 series airplanes); 
or Boeing Service Bulletin 727-52-79, Revision 4, dated June 19, 
1981, or Boeing Service Bulletin 727-52-79, Revision 5, dated June 
17, 1983, or Boeing Service Bulletin 727-52A0079, Revision 6, dated 
January 11, 1990 (for Model 727 series airplanes); as applicable.

Repetitive Inspections

    (b) Repeat the inspection required by paragraph (a) of this AD 
at the times specified in paragraph (b)(1), (b)(2) or (b)(3) of this 
AD; as applicable; until accomplishment of the modification required 
by paragraph (d) of this AD.
    (1) Repeat the detailed visual inspection at intervals not to 
exceed 500 landings.
    (2) Repeat the eddy current inspection at intervals not to 
exceed 750 landings.
    (3) Repeat the X-ray inspection at intervals not to exceed 1,000 
landings.

Repair

    (c) If any cracking is detected during any inspection required 
by paragraph (a) or (b) of this AD: Prior to further flight, repair 
any cracks detected in accordance with Boeing Service Bulletin 2999, 
Revision 3, dated January 12, 1972, or Revision 4, dated January 31, 
1991 (for Model 707 series airplanes); or Boeing Service Bulletin 
727-52-79, Revision 4, dated June 19, 1981, or Boeing Service 
Bulletin 727-52-79, Revision 5, dated June 17, 1983, or Boeing 
Service Bulletin 727-52A0079, Revision 6, dated January 11, 1990 
(for Model 727 series airplanes); as applicable.

Optional Terminating Action

    (d) Modification of the main cargo door in accordance with Part 
II, Option 1 or Option 2, as applicable, of the Accomplishment 
Instructions of Boeing Service Bulletin 2999, Revision 3, dated 
January 12, 1972, or Revision 4, dated January 31, 1991 (for Model 
707 series airplanes); or Boeing Service Bulletin 727-52-79, 
Revision 4, dated June 19, 1981, or Boeing Service Bulletin 727-52-
79, Revision 5, dated June 17, 1983, or Boeing Service Bulletin 727-
52A0079, Revision 6, dated January 11, 1990 (for Model 727 series 
airplanes); as applicable; constitutes terminating action for the 
requirements of paragraphs (a) and (b) of this AD.

New Requirements of this AD:

Post-Repair/Post-Mod Repetitive Inspections

    (e) For Model 727 series airplanes: Within 27,000 flight cycles 
after accomplishment of the repair specified in paragraph (c) of 
this AD, and/or the modification specified in paragraph (d) of this 
AD, as applicable; or within 1,000 flight cycles after the effective 
date of this AD; whichever occurs later; accomplish the requirements 
of paragraph (e)(1) or (e)(2) of this AD, as applicable.
    (1) For airplanes that have accomplished the modification 
specified in Part II of the Accomplishment Instructions of Boeing 
Service Bulletin 727-52-79, Revision 4, dated June 19, 1981, or 
Revision 5, dated June 17, 1983; or in Part II, Option 1, of the 
Accomplishment Instructions of Boeing Service Bulletin 727-52A0079, 
Revision 6, dated January 11, 1990: Perform a detailed visual and 
eddy current inspection of the modified area and/or any repaired 
area to detect cracks, in accordance with the service bulletin. 
Repeat the inspections at intervals not to exceed 3,800 flight 
cycles.
    (2) For airplanes that have accomplished the modification 
specified in Part II, Option 2 of the Accomplishment Instructions of 
Boeing Service Bulletin 727-52A0079, Revision 6, dated January 11, 
1990: Perform an internal and external detailed visual inspection of 
the modified area to detect cracks in accordance with the service 
bulletin. Repeat the inspection at intervals not to exceed 3,800 
flight cycles.

Repair

    (f) If any cracking is detected during any inspection required 
by paragraph (e)(1) or (e)(2) of this AD: Prior to further flight, 
repair any cracks detected 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

    (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, 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.
    (2) Alternative methods of compliance approved previously in 
accordance with AD 83-02-09, amendment 39-4549, are approved as 
alternative methods of compliance with this AD.

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


    Note 4: Incorporation of the Boeing Model 707-720 Supplemental 
Structural Inspection

[[Page 75588]]

Document (SSID) into the operator's approved airplane maintenance 
program constitutes an approved alternative method of compliance for 
Model 707 and 720 series airplanes.

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) Except as provided by paragraph (f) of this AD, the actions 
shall be done in accordance with Boeing Service Bulletin 2999, 
Revision 3, dated January 12, 1972; Boeing Service Bulletin 2999, 
Revision 4, dated January 31, 1991; Boeing Service Bulletin 727-52-
79, Revision 4, dated June 19, 1981; Boeing Service Bulletin 727-52-
79, Revision 5, dated June 17, 1983; or Boeing Service Bulletin 727-
52A0079, Revision 6, including Addendum, dated January 11, 1990; as 
applicable. This incorporation by reference was approved by the 
Director of the 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

    (j) 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. 00-30398 Filed 12-1-00; 8:45 am]
BILLING CODE 4910-13-P