Airworthiness Directives; Boeing Model 727 Series Airplanes

[Federal Register Volume 65, Number 175 (Friday, September 8, 2000)]
[Rules and Regulations]
[Pages 54409-54410]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-23042]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-75-AD; Amendment 39-11816; AD 2000-14-07]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 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 
series airplanes. That AD supersedes an earlier airworthiness directive 
to require repetitive inspections to detect cracking of the rear spar 
web or fuel leakage of the wing center section; repair, if necessary; 
and modification of the rear spar web. This document corrects the 
effective date of the earlier, superseded AD, which was stated 
incorrectly in the existing AD. This correction is necessary to ensure 
that operators are advised of the correct effective date of the 
original AD, specifically as it affects the compliance time for a 
certain paragraph of this AD.

DATES: Effective August 17, 2000.
    The incorporation by reference of Boeing Service Bulletin 727-
57A0182, Revision 1, dated February 25, 1999, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of August 17, 2000 (65 FR 43228, July 13, 2000).
    The incorporation by reference of Boeing Alert Service Bulletin 
727-57A0182, dated September 18, 1997, as listed in the regulations, 
was approved previously by the Director of the Federal Register as of 
December 29, 1997 (62 FR 65355, December 12, 1997).

FOR FURTHER INFORMATION CONTACT: Walter 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 July 3, 2000, the Federal Aviation 
Administration (FAA) issued AD 2000-14-07, amendment 39-11816 (65 FR 
43228, July 13, 2000), which applies to certain Boeing Model 727 series 
airplanes. That AD supersedes an earlier airworthiness directive, AD 
97-25-15, amendment 39-10239 (62 FR 65355, December 12, 1997), to 
require repetitive inspections to detect cracking of the rear spar web 
or fuel leakage of the wing center section; repair, if necessary; and 
modification of the rear spar web. That AD was prompted by several 
reports of fuel leakage due to cracking of the rear spar web of the 
wing center section. The actions required by that AD are intended to 
prevent cracking of the rear spar web, which could permit fuel leakage 
into the airflow multiplier, and could result in an electrical short 
that could cause a fire.

Need for the Correction

    The FAA has found that the effective date associated with the 
earlier, superseded AD (AD 97-25-15) was stated incorrectly in 
paragraph (a) of AD 2000-14-07. The compliance time in paragraph (a) of 
AD 2000-14-07, which is a restatement of paragraph (a) of AD 97-25-15, 
reads, ``Prior to the accumulation of 15,000 total flight cycles, or 
within 300 flight cycles after December 27, 1997 (the effective date of 
AD 97-25-15, amendment 39-10239), whichever occurs later.'' The correct 
effective date of AD 97-25-15 is December 29, 1997.
    The FAA has determined that a correction to AD 2000-14-07 is 
necessary. The correction will ensure that operators are advised of the 
correct effective date of the original AD, particularly as its affects 
the compliance time for paragraph (a) of the AD.

Explanation of Additional Error

    In AD 2000-14-07, Item 2. under the section ``Adoption of the 
Amendment'' reads, ``Section 39.13 is amended by removing amendment 39-
10239 (62 FR 65355, December 29, 1997).'' The referenced date should be 
December 12, 1997, which is the date that AD 97-25-15 was published in 
the Federal Register. This section is not restated in this document; 
therefore, no change to this AD is necessary in this regard.

Correction of Publication

    This document corrects the error in paragraph (a) 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 August 17, 2000.
    Since this action only corrects a calendar date that was referenced 
incorrectly, 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):

2000-14-07  Boeing: Amendment 39-11816. Docket 99-NM-75-AD.

    Applicability: Model 727 series airplanes having line numbers 
858 through 864 inclusive, 867 through 869 inclusive, 872 through 
883 inclusive, and 885 through 1832 inclusive; 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)(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 prevent cracking of the rear spar web, which could permit 
fuel leakage into the

[[Page 54410]]

airflow multiplier, and could result in an electrical short that 
could cause a fire, accomplish the following:

Restatement of the Requirements of AD 97-25-15

Inspections

    (a) Prior to the accumulation of 15,000 total flight cycles, or 
within 300 flight cycles after December 29, 1997 (the effective date 
of AD 97-25-15, amendment 39-10239), whichever occurs later: 
Accomplish the inspections specified in either paragraph (a)(1) or 
(a)(2) of this AD, in accordance with Boeing Alert Service Bulletin 
727-57A0182, dated September 18, 1997, or Boeing Service Bulletin 
727-57A0182, Revision 1, dated February 25, 1999. For purposes of 
the AD, the access panels specified in the alert service bulletin 
need not be removed; the access panels need only be opened.

    Note 2: The fuel tank of the wing center section may be filled 
with fuel to assist in detecting cracking or fuel leakage during the 
accomplishment of the visual inspections required by this AD.

    (1) Perform a visual inspection using a borescope or mirror to 
detect cracking of the rear spar web and/or fuel leakage of the wing 
center section between right body buttock line (BBL) 40 and left BBL 
40, in accordance with Part I of the Accomplishment Instructions of 
the service bulletin. Thereafter, repeat this inspection at 
intervals not to exceed 300 flight cycles. Or
    (2) Perform an ultrasonic and high frequency eddy current (HFEC) 
inspection to detect cracking of the rear spar web of the wing 
center section between right BBL 40 and left BBL 40, in accordance 
with Part II of the Accomplishment Instructions of the service 
bulletin. Thereafter, repeat this inspection at intervals not to 
exceed 3,000 flight cycles.

Repair

    (b) If any cracking of the rear spar web and/or fuel leakage of 
the wing center section is detected between right BBL 40 and left 
BBL 40 near the upper machined land radius, prior to further flight, 
repair in accordance with Part III of the Accomplishment 
Instructions in Boeing Alert Service Bulletin 727-57A0182, dated 
September 18, 1997, or Boeing Service Bulletin 727-57A0182, Revision 
1, dated February 25, 1999. Accomplishment of this repair 
constitutes terminating action for the repetitive inspection 
requirements of this AD.
    (c) If any cracking of the rear spar web and/or fuel leakage of 
the wing center section is detected that is outside the area 
specified in paragraph (b) of this AD, prior to further flight, 
repair in accordance with a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate; 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.

New Requirements of This AD

Modification

    (d) Prior to the accumulation of 60,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later, accomplish an ultrasonic and HFEC inspection 
in accordance with the requirements of paragraph (a)(2) of this AD.
    (1) If no cracking is detected, prior to further flight, modify 
the rear spar web of the center section of the fuel tank between 
right BBL 40 and left BBL 40, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 727-57A0182, dated 
September 18, 1997, or Boeing Service Bulletin 727-57A0182, Revision 
1, dated February 25, 1999. Accomplishment of this modification 
constitutes terminating action for the repetitive inspection 
requirements of this AD.
    (2) If any cracking is detected, prior to further flight, repair 
and modify the rear spar web in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 727-57A0182, dated 
September 18, 1997, or Boeing Service Bulletin 727-57A0182, Revision 
1, dated February 25, 1999. Accomplishment of this modification 
constitutes terminating action for the repetitive inspection 
requirements of this AD.

Alternative Methods of Compliance

    (e)(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 97-25-15, amendment 39-10239, 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.

Special Flight Permits

    (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, provided the 
limitations specified in paragraphs (f)(1) through (f)(6) of this AD 
are included in the special flight permit:
    ``(1) Required trip and reserve fuel must be carried in the No. 
1 and No. 3 outer wing tanks.
    (2) Wing center tank No. 2 must be empty of fuel.
    (3) The fuel system must be checked for normal operation prior 
to flight by verifying that all boost pumps are operational; 
configuring the fuel system by turning on all boost pumps in the 
No.'s 1 and 3 outer wing tanks and by opening all crossfeed valve 
selectors; and by confirming that fuel is not bypassing tank No. 2 
check valves by observing that there is not leakage into tank No. 2.
    (4) Maintain a minimum of 5,300 pounds of fuel in tanks No. 1 
and No. 3 to prevent uncovering the fuel bypass valve.
    (5) The fuel quantity indication system must be operational in 
all three tanks.
    (6) The effects of loading fuel only in the wing tanks on the 
airplane weight and balance must be considered and accounted for.''

Incorporation by Reference

    (g) Except as provided by paragraph (c) of this AD, the actions 
shall be done in accordance with Boeing Alert Service Bulletin 727-
57A0182, dated September 18, 1997; or Boeing Service Bulletin 727-
57A0182, Revision 1, dated February 25, 1999.
    (1) The incorporation by reference of Boeing Service Bulletin 
727-57A0182, Revision 1, dated February 25, 1999, was approved 
previously by the Director of the Federal Register as of August 17, 
2000 (65 FR 43228, July 13, 2000).
    (2) The incorporation by reference of Boeing Alert Service 
Bulletin 727-57A0182, dated September 18, 1997, was approved 
previously by the Director of the Federal Register as of December 
29, 1997 (62 FR 65355, December 12, 1997).
    (3) 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) The effective date of this amendment remains August 17, 
2000.

    Issued in Renton, Washington, on September 1, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-23042 Filed 9-7-00; 8:45 am]
BILLING CODE 4910-13-P

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