

[Federal Register: December 17, 2007 (Volume 72, Number 241)]
[Rules and Regulations]               
[Page 71216-71218]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17de07-8]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28942; Directorate Identifier 2007-NM-093-AD; 
Amendment 39-15306; AD 2007-26-04]
RIN 2120-AA64

 
Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Boeing Model 737-100, -200, -200C, -300, -400, and -500 series 
airplanes. This AD requires repetitive detailed and high-frequency eddy 
current inspections for cracking around the heads of the fasteners on 
the forward fastener row of certain areas of the station (STA) 259.5 
circumferential butt splice, and repair if necessary. This AD also 
requires a preventive modification, which eliminates the need for the 
repetitive inspections. This AD results from a report that an operator 
found multiple cracks in the fuselage skin of a Model 737-200 airplane, 
at the forward fastener row of the STA 259.5 circumferential butt 
splice between stringers 19 and 24. We are issuing this AD to prevent 
cracking of the STA 259.5 circumferential butt splice, which could 
result in loss of structural integrity of the fuselage skin and 
possible loss of cabin pressure.

DATES: This AD is effective January 22, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 22, 
2008.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Management Facility 

between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Docket Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building, Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6447; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness

[[Page 71217]]

directive (AD) that would apply to certain Boeing Model 737-100, -200, 
-200C, -300, -400, and -500 series airplanes. That NPRM was published 
in the Federal Register on August 16, 2007 (72 FR 45949). That NPRM 
proposed to require repetitive detailed and high-frequency eddy current 
inspections for cracking around the heads of the fasteners on the 
forward fastener row of certain areas of the station (STA) 259.5 
circumferential butt splice, and repair if necessary. That NPRM also 
proposed to require a preventive modification, which would eliminate 
the need for the repetitive inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Boeing supports the NPRM.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    There are about 2,150 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD, at an average labor rate of $80 
per work hour. Required parts will be supplied by the operator.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                           Number of U.S.-
              Action                  Work hours      Cost per airplane      registered          Fleet cost
                                                                              airplanes
----------------------------------------------------------------------------------------------------------------
Inspection........................               5  $400, per inspection              654  $261,600, per
                                                     cycle.                                 inspection cycle.
Preventive modification...........              24  $1,920...............             654  $1,255,680.
----------------------------------------------------------------------------------------------------------------

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

    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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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 adding the following new AD:

2007-26-04 Boeing: Amendment 39-15306. Docket No. FAA-2007-28942; 
Directorate Identifier 2007-NM-093-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective January 22, 
2008.

Affected ADs

    (b) Accomplishing repairs and modifications described in 
paragraphs (f) and (g) of this AD is considered acceptable for 
compliance with repair requirements of paragraphs (f) and (g) of AD 
92-25-09, amendment 39-8424, for the areas of the station (STA) 
259.5 circumferential butt splice only.

Applicability

    (c) This AD applies to Boeing Model 737-100, -200, -200C, -300, 
-400, and -500 series airplanes, certificated in any category, as 
identified in Boeing Special Attention Service Bulletin 737-53-1267, 
dated November 28, 2006.

Unsafe Condition

    (d) This AD results from a report that an operator found 
multiple cracks in the fuselage skin of a Model 737-200 airplane, at 
the forward fastener row of the STA 259.5 circumferential butt 
splice between stringers 19 and 24. We are issuing this AD to 
prevent cracking of the STA 259.5 circumferential butt splice, which 
could result in loss of structural integrity of the fuselage skin 
and possible loss of cabin pressure.

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.

Inspections

    (f) At the applicable initial compliance time specified in 
paragraph 1.E. ``Compliance'' of Boeing Special Attention Service 
Bulletin 737-53-1267, dated November 28, 2006, except as provided by 
paragraph (j) of this AD: Do detailed and high-frequency eddy 
current inspections for cracking around the heads of the fasteners 
on the forward fastener row of certain areas of the STA 259.5 
circumferential butt splice, by doing all of the actions specified 
in Part 1 of the Accomplishment Instructions of the service 
bulletin, except as provided by paragraph (i) of this AD. Repeat the 
inspections thereafter at the intervals specified in paragraph 1.E. 
of the service bulletin. Doing the preventive modification specified 
in paragraph (h) of this AD terminates the repetitive inspection 
requirements of this paragraph.

Repair

    (g) If any crack is found during any inspection required by this 
AD, before further flight, repair in accordance with Part 1 of the 
Accomplishment Instructions of Boeing

[[Page 71218]]

Special Attention Service Bulletin 737-53-1267, dated November 28, 
2006.

Preventive Modification

    (h) At the compliance time specified in paragraph 1.E. of Boeing 
Special Attention Service Bulletin 737-53-1267, dated November 28, 
2006, except as provided by paragraph (j) of this AD: Do the 
preventive modification in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-53-
1267, dated November 28, 2006. Doing the preventive modification 
terminates the repetitive inspections required by paragraph (f) of 
this AD.

Modification or Repair Done in Accordance With AD 92-25-09

    (i) Inspections described in paragraph (f) of this AD are not 
required for areas of the STA 259.5 circumferential butt splice that 
have been modified in accordance with the service information 
specified in Table 1 of this AD. (Boeing Service Bulletin 737-53-
1076, Revision 2, dated February 8, 1990; and Revision 4, dated 
September 26, 1991; are cited as appropriate sources of service 
information for doing certain requirements of AD 92-25-09.)

                                          Table 1.--Service Information
----------------------------------------------------------------------------------------------------------------
       Boeing Service Bulletin--              Revision level--                          Date--
----------------------------------------------------------------------------------------------------------------
737-53-1076............................  4.........................  September 26, 1991.
737-53-1076............................  3.........................  September 20, 1990.
737-53-1076............................  2.........................  February 8, 1990.
737-53-1076............................  1.........................  November 23, 1988.
737-53-1076............................  Original..................  October 30, 1986.
----------------------------------------------------------------------------------------------------------------

Compliance Times

    (j) Where Boeing Special Attention Service Bulletin 737-53-1267, 
dated November 28, 2006, specifies compliance times relative to the 
release date of the service bulletin, this AD requires compliance at 
compliance times relative to the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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 Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

Material Incorporated by Reference

    (l) You must use Boeing Special Attention Service Bulletin 737-
53-1267, dated November 28, 2006, to do the actions required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207.
    (3) You may review copies of the service information 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.


    Issued in Renton, Washington, on December 10, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-24335 Filed 12-14-07; 8:45 am]

BILLING CODE 4910-13-P
