[Federal Register Volume 70, Number 47 (Friday, March 11, 2005)]
[Rules and Regulations]
[Pages 12120-12124]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-4826]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19530; Directorate Identifier 2002-NM-274-AD; 
Amendment 39-14008; AD 2005-05-19]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 727 airplanes. That AD 
currently requires repetitive detailed inspections to detect cracking, 
corrosion, and existing stop-drilled repairs of cracking in the upper 
chord of the rear spar of the wing; and repair if necessary. This new 
AD requires new repetitive inspections to detect cracks, corrosion, 
minor surface defects, and existing stop-drilled repairs of cracks in 
the upper and lower chords of the front and rear spars of the wing; and 
repair if necessary. This AD is prompted by our determination that 
further rulemaking action is necessary to require additional actions 
specified in the referenced service bulletin. We are issuing this AD to 
prevent structural failure of the wing and fuel leaks in the airplane 
due to stress corrosion cracking of the wing spar chords.

DATES: This AD becomes effective April 15, 2005.
    On December 18, 2002 (67 FR 71808, December 3, 2002), the Director 
of the Federal Register approved the incorporation by reference of 
Boeing Alert Service Bulletin 727-57A0145, Revision 2, dated October 
24, 2002.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street SW, room PL-401, 
Washington, DC. This docket number is FAA-2004-19530; the directorate 
identifier for this docket is 2002-NM-274-AD.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the 
Federal Aviation Regulations (14 CFR Part 39) with an AD to supersede 
AD 2002-24-05, amendment 39-12970 (67 FR 71808, December 3, 2002). The 
existing AD applies to certain Boeing Model 727 airplanes. The proposed 
AD was published in the Federal Register on November 5, 2004 (69 FR 
64506), to require new repetitive inspections to detect cracks, 
corrosion, minor surface defects, and existing stop-drilled repairs of 
cracks in the upper and lower chords of the front and rear spars of the 
wing; and repair if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that has been 
submitted on the proposed AD. The commenter supports the proposed AD.

Explanation of Change to Model Designation

    We have revised the subject heading of the existing AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

Changes to Delegation Authority

    Boeing has received a Delegation Option Authorization (DOA). We 
have revised this final rule to delegate the authority to approve an 
alternative method of compliance for any repair required by this AD to 
the Authorized Representative for the Boeing DOA Organization rather 
than the Designated Engineering Representative (DER).

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been submitted, and determined that air safety and the 
public interest require adopting the AD with the change described 
previously. We have determined that this change will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 1,426 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 946 airplanes of U.S. 
registry.
    For Group 1 airplanes identified in the service bulletin, the 
actions (Part 1 of the Accomplishment Instructions of the service 
bulletin) that are required by AD 2002-24-05 and retained in this AD 
take about 8 work hours per airplane, at an average labor rate of $65 
per work hour. Based on these figures, the estimated cost of the 
currently required actions is $520 per airplane.
    The following table provides the estimated costs for U.S. operators 
to comply with the new actions required by this AD. The average labor 
rate is $65 per work hour.

[[Page 12121]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                                           Per airplane
                                                                                                                                             cost, per
                For airplanes identified in the service bulletin as--                             Actions in--             Work hours--     inspection
                                                                                                                                              cycle--
--------------------------------------------------------------------------------------------------------------------------------------------------------
Group 1..............................................................................  Part 2 of the Accomplishment                   30          $1,950
                                                                                        Instructions of the service
                                                                                        bulletin.
Group 1..............................................................................  Part 3 of the Accomplishment                   21           1,365
                                                                                        Instructions of the service
                                                                                        bulletin.
Group 1..............................................................................  Part 4 of the Accomplishment                   68           4,420
                                                                                        Instructions of the service
                                                                                        bulletin.
Group 1..............................................................................  Part 8 of the Accomplishment                    8             520
                                                                                        Instructions of the service
                                                                                        bulletin.
Group 1..............................................................................  Part 9 of the Accomplishment                   30           1,950
                                                                                        Instructions of the service
                                                                                        bulletin.
Group 2..............................................................................  Part 5 of the Accomplishment                   52           3,380
                                                                                        Instructions of the service
                                                                                        bulletin.
Group 2..............................................................................  Part 6 of the Accomplishment                  110           7,150
                                                                                        Instructions of the service
                                                                                        bulletin.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by removing amendment 39-12970 (67 FR 
71808, December 3, 2002), and by adding the following new airworthiness 
directive (AD):

2005-05-19 Boeing: Amendment 39-14008. Docket No. FAA-2004-19530; 
Directorate Identifier 2002-NM-274-AD.

Effective Date

    (a) This AD becomes effective April 15, 2005.

Affected ADs

    (b) This AD supersedes AD 2002-24-05, amendment 39-12970.

Applicability

    (c) This AD applies to Boeing Model 727, 727C, 727-100, -100C, -
200, and -200F series airplanes, line numbers 1 through 1832 
inclusive; certificated in any category.

Unsafe Condition

    (d) This AD was prompted by our determination that further 
rulemaking action is necessary to require additional actions 
specified in the referenced service bulletin. We are issuing this AD 
to prevent structural failure of the wing and fuel leaks in the 
airplane due to stress corrosion cracking of the wing spar chords.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin References

    (f) The term ``the service bulletin,'' as used in this AD, means 
Boeing Alert Service Bulletin 727-57A0145, Revision 2, dated October 
24, 2002.

Inspection Requirements of AD 2002-24-05, Amendment 39-12970

Inspection

    (g) For airplanes specified as ``Group 1'' airplanes in the 
service bulletin: Within 20 years after the date of manufacture or 
within 90 days after December 18, 2002 (the effective date of AD 
2002-24-05, amendment 39-12970), whichever occurs later, perform an 
external detailed inspection for cracking, corrosion, and existing 
stop-drilled repairs of cracking in the upper chord on the rear spar 
from Wing Butt Line (WBL) 70.5 through WBL 249.3, per the service 
bulletin, paragraph 3.B, ``Work Instructions,'' Part 1. Thereafter, 
repeat the inspection at intervals not to exceed 2 years.

    Note 1: For the purposes of this AD, a detailed inspection is 
``an intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirrors, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


[[Page 12122]]



New Actions Required by This AD

Inspections Specified in Parts 2 Through 6, and 8 and 9 of the 
Service Bulletin

    (h) Accomplish the applicable inspection(s) specified in 
paragraphs (h)(1) through (h)(7) of this AD at the later of the 
applicable times specified in the ``Threshold'' and ``Grace Period'' 
columns in Table 1 of this AD, and repeat the inspection(s) at the 
time specified in the ``Repetitive Interval'' column of Table 1 of 
this AD. Accomplishment of the inspection required by paragraph 
(h)(1) of this AD terminates the repetitive inspection requirements 
of paragraph (g) of this AD.

   Table 1.--Compliance Times for Inspections Specified in Parts 2 Through 6, and 8 and 9 of Service Bulletin
----------------------------------------------------------------------------------------------------------------
 For airplanes identified in the                                              Repetitive
      service bulletin as--           Threshold--       Grace period--        interval--             Do--
----------------------------------------------------------------------------------------------------------------
(1) Group 1.....................  Before 20 years     Within 1 year       None..............  A high frequency
                                   since the date of   after the                               eddy current
                                   issuance of the     effective date of                       (HFEC) inspection
                                   original            this AD.                                and detailed
                                   Airworthiness                                               inspection of the
                                   Certificate or                                              upper chord the
                                   the date of                                                 rear spar from
                                   issuance of the                                             WBL 70.5 to the
                                   original Export                                             wing tip for
                                   Certificate of                                              cracks,
                                   Airworthiness.                                              corrosion, minor
                                                                                               surface defects,
                                                                                               and existing stop-
                                                                                               drilled repairs
                                                                                               of cracking, in
                                                                                               accordance with
                                                                                               paragraph 3.B.,
                                                                                               Work
                                                                                               Instructions,
                                                                                               Part 2, of the
                                                                                               Accomplishment
                                                                                               Instructions of
                                                                                               the service
                                                                                               bulletin.
(2) Group 1.....................  Before 20 years     Within 2 years      At intervals not    A detailed
                                   since the date of   after the           to exceed 2 years.  inspection of the
                                   issuance of the     effective date of                       upper and lower
                                   original            this AD.                                chord of the
                                   Airworthiness                                               front spar and
                                   Certificate or                                              the lower chord
                                   the date of                                                 of the rear spar
                                   issuance of the                                             from WBL 70.5 to
                                   Original Export                                             the wing tip for
                                   Certificate of                                              cracks,
                                   Airworthiness.                                              corrosion, minor
                                                                                               surface defects,
                                                                                               and existing stop-
                                                                                               drilled repairs
                                                                                               of cracking
                                                                                               (initial
                                                                                               inspection only),
                                                                                               in accordance
                                                                                               with paragraph
                                                                                               3.B., Work
                                                                                               Instructions,
                                                                                               Part 3, of the
                                                                                               Accomplishment
                                                                                               Instructions of
                                                                                               the service
                                                                                               bulletin.
(3) Group 1.....................  Before 20 years     Within 4 years      At intervals not    An HFEC inspection
                                   since the date of   after the           to exceed 4 years.  of the upper and
                                   issuance of the     effective date of                       lower chords of
                                   original            this AD.                                the rear spar
                                   Airworthiness                                               from WBL 70.5 to
                                   Certificate or                                              the wing tip for
                                   the date of                                                 cracks,
                                   issuance of the                                             corrosion, minor
                                   original Export                                             surface defects,
                                   Certificate of                                              and existing stop-
                                   Airworthiness.                                              drilled repairs
                                                                                               of cracking
                                                                                               (initial
                                                                                               inspection only),
                                                                                               in accordance
                                                                                               with paragraph
                                                                                               3.B., Work
                                                                                               Instructions,
                                                                                               Part 4, of the
                                                                                               Accomplishment
                                                                                               Instructions of
                                                                                               the service
                                                                                               bulletin.
(4) Group 1.....................  Within 2 years      None..............  At intervals not    A detailed
                                   after doing the                         to exceed 2 years.  inspection of the
                                   actions required                                            upper chord of
                                   by paragraph                                                the rear spar WBL
                                   (h)(1) of this AD.                                          70.5 to the wing
                                                                                               tip for cracks,
                                                                                               corrosion, minor
                                                                                               surface defects,
                                                                                               and existing stop-
                                                                                               drilled repairs
                                                                                               of cracking
                                                                                               (initial
                                                                                               inspection only),
                                                                                               in accordance
                                                                                               with paragraph
                                                                                               3.B., Work
                                                                                               Instructions,
                                                                                               Part 8, of the
                                                                                               Accomplishment
                                                                                               Instructions of
                                                                                               the service
                                                                                               bulletin.

[[Page 12123]]

 
(5) Group 1.....................  Within 4 years      None..............  At intervals not    An HFEC inspection
                                   after doing the                         to exceed 4 years.  of doing the not
                                   actions required                                            to the upper
                                   by paragraph                                                chord actions
                                   (h)(1) of this AD.                                          exceed 4 of the
                                                                                               rear spar
                                                                                               required by years
                                                                                               from WBL 70.5 to
                                                                                               paragraph the
                                                                                               wing tip for
                                                                                               (h)(1) of cracks,
                                                                                               this AD
                                                                                               corrosion, minor
                                                                                               surface defects,
                                                                                               and existing stop-
                                                                                               drilled repairs
                                                                                               of cracking
                                                                                               (initial
                                                                                               inspection only),
                                                                                               in accordance
                                                                                               with paragraph
                                                                                               3.B., Work
                                                                                               Instructions,
                                                                                               Part 9, of the
                                                                                               Accomplishment
                                                                                               Instructions of
                                                                                               the service
                                                                                               bulletin.
(6) Group 2.....................  Before 20 years     Within 2 years      At intervals not    An exterior
                                   since the date of   after the           to exceed 2 years.  detailed
                                   issuance of the     effective date of                       inspection of the
                                   original            this AD.                                upper and lower
                                   Airworthiness                                               chords of the
                                   Certificate or                                              front and rear
                                   the date of                                                 spars from WBL
                                   issuance of the                                             70.5 to the wing
                                   original Export                                             tip for cracks,
                                   Certificate of                                              corrosion, minor
                                   Airworthiness.                                              surface defects,
                                                                                               and existing stop-
                                                                                               drilled repairs
                                                                                               of cracking
                                                                                               (initial
                                                                                               inspection only),
                                                                                               in accordance
                                                                                               with paragraph
                                                                                               3.B., Work
                                                                                               Instructions,
                                                                                               Part 5, of the
                                                                                               Accomplishment
                                                                                               Instructions of
                                                                                               the service
                                                                                               bulletin.
(7) Group 2.....................  Before 20 years     Within 4 years      At intervals not    An HFEC inspection
                                   since the date of   after the           to exceed 4 years.  of the upper and
                                   issuance of the     effective date of                       lower chords of
                                   original            this AD.                                the front and
                                   Airworthiness                                               rear spars from
                                   Certificate or                                              WBL 70.5 to the
                                   the date of                                                 wing tip for
                                   issuance of the                                             cracks,
                                   original Export                                             corrosion, minor
                                   Certificate of                                              surface defects,
                                   Airworthiness.                                              and existing stop-
                                                                                               drilled repairs
                                                                                               of cracking
                                                                                               (initial
                                                                                               inspection only),
                                                                                               in accordance
                                                                                               with paragraph
                                                                                               3.B., Work
                                                                                               Instructions,
                                                                                               Part 6, of the
                                                                                               Accomplishment
                                                                                               Instructions of
                                                                                               the service
                                                                                               bulletin.
----------------------------------------------------------------------------------------------------------------

Corrective Actions

    (i) If any crack, corrosion, or minor surface defect is detected 
during any inspection required by this AD, before further flight, do 
the applicable corrective actions in accordance with Part 7 of the 
Accomplishment Instructions of the service bulletin, except as 
provided by paragraph (j) of this AD.
    (j) If any crack or corrosion is detected during any inspection 
required by this AD that exceeds the limits specified in the service 
bulletin, and the bulletin specifies to contact Boeing for 
appropriate action: Before 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 
certification basis of the airplane approved by an Authorized 
Representative for the Boeing Delegation Option Authorization 
Organization who has been authorized by the Manager, Seattle ACO, to 
make such findings. For a repair method to be approved, the approval 
must specifically reference this AD.
    (k) If any existing stop-drilled repair of previous cracking is 
detected during any inspection required by this AD, before further 
flight, permanently repair crack in accordance with paragraph 3.B., 
Work Instructions, Part 7, paragraph 2., ``Crack Repair'' of the 
Accomplishment Instructions of the service bulletin.
    (l) Before further flight following any inspection or repair 
required by this AD, apply a wet layer of BMS 3-23 organic corrosion 
inhibiting compound or Boeing equivalent, in accordance with the 
Accomplishment Instructions of the service bulletin.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2002-24-05, amendment 39-12970, are

[[Page 12124]]

approved as alternative methods of compliance with this AD.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Seattle ACO, to make such findings. For a repair method to be 
approved, the approval must specifically reference this AD.

Material Incorporated by Reference

    (n) You must use Boeing Alert Service Bulletin 727-57A0145, 
Revision 2, dated October 24, 2002, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register previously approved the incorporation by 
reference of this document as of December 18, 2002 (67 FR 71808, 
December 3, 2002). For copies of the service information, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207. For information on the availability of this material at 
the National Archives and Records Administration (NARA), call (202) 
741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. You may view the AD 
docket at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW, room PL-401, Nassif Building, 
Washington, DC.

    Issued in Renton, Washington, on March 2, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-4826 Filed 3-10-05; 8:45 am]
BILLING CODE 4910-13-P