[Federal Register Volume 67, Number 92 (Monday, May 13, 2002)]
[Rules and Regulations]
[Pages 31943-31945]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-11803]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-105-AD; Amendment 39-12703; AD 2002-07-09]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD that applies to certain Boeing Model 727, 
727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes. That 
AD currently requires repetitive inspections to find cracking of the 
lower skin panel at the lower row of fasteners in certain lap joints of 
the fuselage, and repair, if necessary. This document corrects a 
typographical error in the supplemental type certificate (STC) number 
specified in paragraph (i) of that AD. This correction is necessary to 
ensure that the correct STC number is specified and operators of 
affected airplanes are advised of all applicable actions.

DATES: Effective May 17, 2002.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of May 17, 2002 (67 FR 17923, April 12, 2002).

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: On April 2, 2002, the Federal Aviation 
Administration (FAA) issued AD 2002-07-09, amendment 39-12703 (67 FR 
17923, April 12, 2002), which applies to all Boeing Model 727, 727C, 
727-100, 727-100C, 727-200, and 727-200F series airplanes. That AD 
currently requires repetitive inspections to find cracking of the lower 
skin panel at the lower row of fasteners in certain lap joints of the 
fuselage, and repair, if necessary. That AD was prompted by the FAA's 
determination that, in light of additional crack findings, certain 
modifications of the fuselage lap joints are necessary. The actions 
required by that AD are intended to find and fix fatigue cracking of 
the fuselage lap joints, which could result in sudden fracture and 
failure of the lower skin lap joints, and rapid decompression of the 
airplane.

Need for the Correction

    The FAA notes that there is a typographical error in the STC number 
specified in paragraph (i) of the AD.
    The FAA has determined that a correction to AD 2002-07-09 is 
necessary to correctly identify the STC number.

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains May 17, 2002.
    Since this action only corrects a typographical error, it has no 
adverse economic impact and imposes no additional burden on any person. 
Therefore, the FAA has determined that notice and public procedures are 
unnecessary.

List of Subjects in 14 CFR Part 39

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

Adoption of the Correction

    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  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2002-07-09  Boeing: Amendment 39-12703. Docket 99-NM-105-AD.

    Applicability: Model 727 series airplanes, as listed in Boeing 
Service Bulletin 727-53A0222, Revision 1, including Appendix A, 
dated March 15, 2001, 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 (l)(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 find and fix fatigue cracking in the lower skin panel at the 
lower row of fasteners of the fuselage lap joints, which could 
result in sudden fracture and failure of the lap joints, and rapid 
decompression of the airplane; accomplish the following:

Initial and Repetitive Inspections

    (a) Do either an external low frequency eddy current (LFEC) 
inspection to find cracking, or both internal detailed and medium 
frequency eddy current (MFEC) inspections to find cracking or 
corrosion, in the lower skin panels of the lower row of fasteners of 
the fuselage lap joints per Part I of the Accomplishment 
Instructions of Boeing Service Bulletin 727-53A0222, Revision 1, 
including Appendix A, dated March 15, 2001. Do the applicable 
inspection at the earlier of the times specified in paragraphs 
(a)(1) and (a)(2) of this AD on the lap joints identified in Tables 
A through H and J through N of Section 1.E., ``Compliance,'' of 
Paragraph 1, Planning Information, of the service bulletin. Except 
as provided by paragraph (b) of this AD, after doing the applicable 
initial inspection, repeat that inspection at the intervals 
specified in

[[Page 31944]]

Tables A through G or J through N of the service bulletin.
    (1) At the latest of the times specified for the initial 
inspection in Tables A through H (for Groups 1, 2, 3, and 5 
airplanes), or Tables J through N (for Groups 3 and 4 airplanes), as 
applicable, of Section 1.E., ``Compliance,'' of the service 
bulletin, except where the compliance time in the service bulletin 
specifies a compliance time interval based on ``the release of this 
service bulletin,'' this AD requires compliance within the interval 
specified in the service bulletin ``after the effective date of this 
AD.''
    (2) Within 600 flight cycles after the last LFEC inspection or 
7,000 flight cycles after the last MFEC inspection, if any, is 
accomplished in accordance with AD 99-04-22, amendment 39-11047.

    Note 2: Groups 1-5 are defined in the effectivity section of the 
service bulletin.


    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 find 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.''

    (b) For Model 727-200 series airplanes: The repetitive 
inspection intervals for lap joints identified in Table H of Section 
1.E., ``Compliance,'' of Paragraph 1, Planning Information, of 
Boeing Service Bulletin 727-53A0222, Revision 1, including Appendix 
A, dated March 15, 2001, decrease with increasing flight cycles. 
Perform the repetitive inspections listed in Table H of the service 
bulletin at the thresholds and intervals specified in paragraph 
(b)(1), (b)(2), (b)(3), or (b)(4) of this AD, as applicable.

    Note 4: Table H of Boeing Service Bulletin 727-53A0222, Revision 
1, has different inspection procedures for airplanes that have 
accumulated fewer than 35,000 total flight cycles, and airplanes 
that have accumulated 35,000 or more, but fewer than 45,000 total 
flight cycles.

    (1) If, at the time of the most recent inspection required by 
paragraph (a) or (b) of this AD, the airplane has accumulated fewer 
than 35,000 total flight cycles: Perform LFEC inspections at 
intervals not to exceed 600 flight cycles, or detailed internal 
visual and MFEC inspections at intervals not to exceed 7,000 flight 
cycles.
    (2) If, at the time of the most recent inspection required by 
paragraph (a) or (b) of this AD, the airplane has accumulated 35,000 
or more, but fewer than 45,000 total flight cycles: Perform LFEC 
inspections at intervals not to exceed 600 flight cycles, or 
detailed internal visual and MFEC inspections at intervals not to 
exceed 7,000 flight cycles.
    (3) If, at the time of the most recent inspection required by 
paragraph (a) or (b) of this AD, the airplane has accumulated 45,000 
or more, but fewer than 55,000 total flight cycles: Perform detailed 
internal visual and MFEC inspections at intervals not to exceed 
2,000 flight cycles.
    (4) If, at the time of the most recent inspection required by 
paragraph (a) or (b) of this AD, the airplane has accumulated 55,000 
or more total flight cycles: Perform LFEC inspections at intervals 
not to exceed 300-flight-cycle intervals.

    Note 5: Inspections done prior to the effective date of this AD 
per Boeing Alert Service Bulletin 727-53A0222, dated July 27, 2000, 
are considered acceptable for compliance with the applicable action 
specified in this amendment.

Compliance Plan

    (c) For airplanes on which the modification required by 
paragraph (d) of this AD has not been done as of the effective date 
of this AD: Within 3 months after the effective date of this AD, 
submit a plan to the FAA identifying a schedule for compliance with 
paragraph (d) of this AD. This schedule must include, for each of 
the operator's affected airplanes, the estimated dates when the 
required actions will be accomplished. For the purposes of this 
paragraph, ``FAA'' means the Principal Maintenance Inspector (PMI) 
for operators that are assigned a PMI, or the cognizant Flight 
Standards District Office for other operators. Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.

    Note 6: Operators are not required to submit revisions to the 
compliance plan required by paragraph (c) of this AD to the FAA.

Modification/Post-Modification Inspections

    (d) For Model 727-200 series airplanes: Do the modification 
listed in Table H of Section 1.E., ``Compliance,'' of Paragraph 1, 
Planning Information, of Boeing Service Bulletin 727-53A0222, 
Revision 1, including Appendix A, dated March 15, 2001; per Part II 
of the Accomplishment Instructions of the service bulletin, at the 
threshold specified in paragraph (d)(1), (d)(2), or (d)(3) of this 
AD, as applicable. Within 35,000 flight cycles after doing the 
modification, do the post-modification inspections for cracking in 
the skin, per Part III of the Accomplishment Instructions of the 
service bulletin. Accomplishment of this paragraph terminates the 
repetitive inspections required by paragraph (b) of this AD.
    (1) For airplanes that have accumulated fewer than 35,000 total 
flight cycles on the effective date of the AD: Accomplish the 
modification prior to 48,000 total flight cycles.
    (2) For airplanes that have accumulated 35,000 or more, but 
fewer than 55,000 total flight cycles on the effective date of the 
AD: Accomplish the modification prior to 55,000 total flight cycles, 
or within 2,000 flight cycles after the effective date of this AD, 
whichever is later.
    (3) For airplanes that have accumulated 55,000 or more total 
flight cycles on the effective date of the AD: Accomplish the 
modification within 2,000 flight cycles after the effective date of 
this AD.

Repair

    (e) If any cracking or corrosion is found during any inspection 
required by paragraph (a), (b), or (d) of this AD: Before further 
flight, repair per Boeing Service Bulletin 727-53A0222, Revision 1, 
including Appendix A, dated March 15, 2001. Where the service 
bulletin specifies to contact Boeing for repair instructions, repair 
per a method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA; or per data meeting the type certification basis 
of the airplane approved by a Boeing Company DER 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 approval letter must specifically 
reference this AD.

Concurrent Modifications

    (f) For Model 727-200 series airplanes modified per supplemental 
type certificate (STC) SA1368SO or SA1797SO: Concurrent with the 
modification of the fuselage lap joints required by paragraph (d) of 
this AD, do the inspection for cracking of the lower row of 
fasteners in the lower skin of the lap joints, and the modification 
specified in Aeronautical Engineers Inc. Service Bulletin AEI 00-01, 
Revision A, dated May 7, 2001, per the service bulletin.
    (g) For Model 727-200 series airplanes modified per STCs 
SA1444SO and SA1509SO: Concurrent with the modification of the 
fuselage lap joints required by paragraph (d) of this AD, do the 
inspection for cracking of the lower row of fasteners in the lower 
skin of the lap joints, and the modification specified in PEMCO 
Service Bulletin 727-53-0007, Revision 1, dated June 6, 2001, per 
the service bulletin.
    (h) For Model 727-200 series airplanes modified per STC 
SA00015AT: Concurrent with the modification of the fuselage lap 
joints required by paragraph (d) of this AD, do the inspection for 
cracking of the lower row of fasteners in the lower skin of the lap 
joints, and the modification specified in Aircraft Technical 
Service, Inc., Service Bulletin ATS 727-001, dated May 7, 2001, per 
the service bulletin.
    (i) For Model 727-200 series airplanes modified per STC 
SA1767SO: Concurrent with the modification of the fuselage lap 
joints required by paragraph (d) of this AD, do the inspection for 
cracking of the lower row of fasteners in the lower skin of the lap 
joints, and the modification specified in Federal Express 
Corporation Service Bulletin 00-029, Revision A, including 
Attachment A, dated May 16, 2001, per the service bulletin.
    (j) Within 2,200 flight cycles after doing the applicable 
modification specified in paragraph (f), (g), (h), or (i) of this 
AD, do the post-modification inspection for cracking in the skin per 
the applicable service bulletin specified in Table 1, below. Repeat 
the applicable inspection after that at intervals not to exceed 
2,200 flight cycles. Table 1 follows:

[[Page 31945]]



                       Table 1.--Service Bulletins
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             Service bulletin                           Date
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Aeronautical Engineers Inc. Service         May 7, 2001.
 Bulletin AEI 00-01, Revision A.
Aircraft Technical Service, Inc., Service   May 7, 2001.
 Bulletin ATS 727-001.
Federal Express Corporation Service         May 16, 2001.
 Bulletin 00-029, Revision A, including
 Attachment A.
PEMCO Service Bulletin, 727-53-0007,        June 6, 2001.
 Revision 1.
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Repair

    (k) If any cracking is found during any inspection required by 
paragraph (f), (g), (h), or (i) of this AD: Before further flight, 
repair per the applicable service bulletin as provided in Table 1 in 
paragraph (j) of this AD. Where cracks exceed the limits provided in 
the service bulletin, and the bulletin specifies to contact the 
provider of the service bulletin for repair instructions, prior to 
further flight, repair per a method approved by the Manager, Seattle 
ACO. If any cracking is found during any inspection required by 
paragraph (j) of this AD: Before further flight, repair per a method 
approved by the Manager, Seattle ACO. For a repair method to be 
approved by the Manager, Seattle ACO, as required by this paragraph, 
the approval letter must specifically reference this AD.

Alternative Methods of Compliance

    (l)(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 PMI, who may add comments 
and then send it to the Manager, Seattle ACO.
    (2) Alternative methods of compliance, approved previously per 
AD 99-04-22, amendment 39-11047, are approved as alternative methods 
of compliance with this AD.

    Note 7: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (m) 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

    (n) Except as provided by paragraphs (c), (e), and (k) of this 
AD, the actions shall be done in accordance with the following 
service bulletins, as applicable:

                       Table 2.--Service Bulletins
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             Service bulletin                           Date
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Aeronautical Engineers Inc. Service         May 7, 2001.
 Bulletin AEI 00-01, Revision A.
Aircraft Technical Service, Inc., Service   May 7, 2001.
 Bulletin ATS 727-001.
Boeing Service Bulletin 727-53A0222,        March 15, 2001.
 Revision 1, including Appendix A.
Federal Express Corporation Service         May 16, 2001.
 Bulletin 00-029, Revision A, including
 Attachment A.
PEMCO Service Bulletin 727-53-0007,         June 6, 2001.
 Revision 1.
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    This incorporation by reference was approved previously by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51 as of May 17, 2002 (67 FR 17923, April 12, 2002). 
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

    (o) The effective date of this amendment remains May 17, 2002.

    Issued in Renton, Washington, on May 6, 2002.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-11803 Filed 5-10-02; 8:45 am]
BILLING CODE 4910-13-P