[Federal Register Volume 75, Number 7 (Tuesday, January 12, 2010)]
[Rules and Regulations]
[Pages 1533-1535]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-30968]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0655; Directorate Identifier 2008-NM-192-AD; 
Amendment 39-16157; AD 2010-01-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747-200F, 747-
200C, 747-400, 747-400D, and 747-400F Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Model 747-200F, 747-200C, 747-400, 747-400D, 
and 747-400F series airplanes. That AD currently requires repetitive 
inspections for cracking of certain fuselage internal structure (i.e., 
Sections 42 and 46 fuselage frames, upper deck floor beams, electronic 
bay access door cutout, nose wheel well, and main entry doors and door 
cutouts), and repair if necessary. This new AD requires additional 
repetitive inspections for cracking of certain fuselage structure 
(i.e., Section 41 fuselage frames where they connect to upper deck 
floor beams, and Section 41 fuselage frames between stringers (S-8 and 
S-12)), and related investigative/corrective actions if necessary. This 
AD also reduces the inspection threshold and repetitive inspection 
intervals for certain airplanes. This AD results from fatigue tests and 
analysis that identified additional areas of the fuselage where fatigue 
cracks can occur. We are issuing this AD to prevent the loss of 
structural integrity of the fuselage, which could result in rapid 
depressurization of the airplane.

DATES: This AD becomes effective February 16, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 16, 
2010.
    The Director of the Federal Register approved the incorporation by 
reference of Boeing Alert Service Bulletin 747-53A2500, dated December 
21, 2004, as of April 6, 2006 (71 FR 10605, March 2, 2006).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail [email protected]; 
Internet https://www.myboeingfleet.com.

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 Document 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: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-05-02, Amendment 
39-14499 (71 FR 10605, March 2, 2006). The existing AD applies to all 
Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F series 
airplanes. That NPRM was published in the Federal Register on July 23, 
2009 (74 FR 36417). That NPRM proposed to continue to require 
repetitive inspections for cracking of certain fuselage internal 
structure (i.e., Sections 42 and 46 fuselage frames, upper deck floor 
beams, electronic bay access door cutout, nose wheel well, and main 
entry doors and door cutouts), and repair if necessary. That NPRM 
proposed to require additional repetitive inspections for cracking of 
certain fuselage structure (i.e., Section 41 fuselage frames where they 
connect to upper deck floor beams, and Section 41 fuselage frames 
between stringer (S-8 and S-12)), and related investigative/corrective 
actions if necessary. That NPRM also proposed to reduce the inspection 
threshold and repetitive inspection intervals for certain airplanes. 
That NPRM resulted from fatigue tests and analysis that identified 
areas of the fuselage where fatigue cracks can occur.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have

[[Page 1534]]

considered the comments that have been received on the NPRM.

Request To Revise References in Paragraph (m)(4) of the NPRM

    Boeing requests that paragraph (m)(4) of the NPRM be revised to 
reference paragraphs (h) and (i)--not paragraphs (c) and (d). Boeing 
states that in AD 2004-07-22 R1, Amendment 39-15326 (73 FR 1052, 
January 7, 2008), paragraph identifiers (c) and (d) were revised to (h) 
and (i).
    We agree. We have revised paragraph (m)(4) of this final rule 
accordingly. In addition, we have revised paragraph (m)(4)(i) of this 
AD to change the reference from paragraph (d) to paragraph (i) of AD 
2004-07-22 R1.
    Boeing also requests that paragraph (m)(4)(ii) of the NPRM be 
revised to add a reference to Boeing Alert Service Bulletin 747-
53A2500, Revision 1, dated September 25, 2008. Boeing states that both 
the original and Revision 1 of Boeing Alert Service Bulletin 747-
53A2500 provide inspections that are an AMOC to AD 2004-07-22 R1.
    We agree for the reasons provided by the commenter. We have revised 
paragraph (m)(4)(ii) of this AD accordingly.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Explanation of Changes Made to This AD

    We have revised this AD to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.

Costs of Compliance

    There are about 640 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. The average labor rate is $80 
per work hour.

                                                 Estimated Costs
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                                                                                 Number of U.S.-
            Action               Work hours         Parts           Cost per       registered       Fleet cost
                                                                    airplane        airplanes
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Inspections (required by AD               260  None required..  $20,800 per                  71  $1,476,800 per
 2006-05-02).                                                    inspection                       inspection
                                                                 cycle.                           cycle.
Inspections of additional                   7  None required..  $560 per                     71  $39,760 per
 areas (new required action).                                    inspection                       inspection
                                                                 cycle.                           cycle.
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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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing Amendment 39-14499 (71 FR 10605, March 2, 2006) and by adding 
the following new airworthiness directive (AD):

2010-01-01 The Boeing Company: Amendment 39-16157. Docket No. FAA-
2009-0655; Directorate Identifier 2008-NM-192-AD.

Effective Date

    (a) This AD becomes effective February 16, 2010.

Affected ADs

    (b) This AD supersedes AD 2006-05-02, Amendment 39-14499.

Applicability

    (c) This AD applies to all The Boeing Company Model 747-200F, 
747-200C, 747-400, 747-400D, and 747-400F series airplanes; 
certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from fatigue tests and analysis that 
identified additional areas of the fuselage where fatigue cracks can 
occur. We are issuing this AD to prevent the loss of structural 
integrity of the fuselage, which could result in rapid 
depressurization of the airplane.

[[Page 1535]]

Compliance

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

Restatement of Requirements of AD 2006-05-02, With Updated Service 
Information and Reduced Compliance Times for Group 8 Airplanes

Inspections

    (g) Do initial and repetitive inspections for fuselage cracks 
using applicable internal and external detailed inspection methods, 
and repair all cracks, by doing all the actions specified in the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2500, dated December 21, 2004; or Revision 1, dated September 25, 
2008; except as required by paragraph (h) or provided by paragraph 
(l) of this AD. After the effective date of this AD, Boeing Alert 
Service Bulletin 747-53A2500, Revision 1, dated September 25, 2008, 
must be used. Do the initial and repetitive inspections at the 
applicable times specified in paragraph (g)(1) or (g)(2) of this AD, 
except as required by paragraph (j) of this AD. Repair any crack 
before further flight after detection.
    (1) For Groups 1 through 7, 9, and 10 identified in Boeing Alert 
Service Bulletin 747-53A2500, Revision 1, dated September 25, 2008: 
Do the initial and repetitive inspections at the times specified in 
paragraph 1.E. of Boeing Alert Service Bulletin 747-53A2500, dated 
December 21, 2004, except as required by paragraph (i) of this AD.
    (2) For Group 8 airplanes identified in Boeing Alert Service 
Bulletin 747-53A2500, Revision 1, dated September 25, 2008: Do the 
initial and repetitive inspections at the applicable time specified 
in paragraph 1.E. of Boeing Alert Service Bulletin 747-53A2500, 
Revision 1, dated September 25, 2008, except as required by 
paragraph (k) of this AD.

Exceptions to Service Bulletin Procedures

    (h) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2500, dated December 
21, 2004; or Revision 1, dated September 25, 2008; specifies to 
contact Boeing for appropriate action: Before further flight, repair 
the crack using a method approved in accordance with the procedures 
specified in paragraph (m) of this AD.
    (i) Where Boeing Alert Service Bulletin 747-53A2500, dated 
December 21, 2004; or Revision 1, dated September 25, 2008; 
specifies a compliance time after the date on the original issue of 
the service bulletin, this AD requires compliance within the 
specified compliance time after April 6, 2006 (the effective date of 
AD 2006-05-02).

New Requirements of This AD

Actions for Additional Areas

    (j) For the additional inspection areas of Groups 1 through 7, 
9, and 10 airplanes, identified in Boeing Alert Service Bulletin 
747-53A2500, Revision 1, dated September 25, 2008: Do initial and 
repetitive inspections for cracking of the inspection areas, and, as 
applicable, repair cracking, by doing all the actions specified in 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2500, Revision 1, dated September 25, 2008; except as 
required by paragraph (h) of this AD. Do the initial and repetitive 
inspections at the times specified in paragraph 1.E. of Boeing Alert 
Service Bulletin 747-53A2500, Revision 1, dated September 25, 2008, 
except as required by paragraph (k) of this AD. Repair all cracking 
before further flight.
    (k) Where Boeing Alert Service Bulletin 747-53A2500, Revision 1, 
dated September 25, 2008, specifies a compliance time after the date 
on Revision 1 of the service bulletin, this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (l) For Group 8 airplanes, inspection of Areas 2 and 5 
identified in Boeing Alert Service Bulletin 747-53A2500, dated 
December 21, 2004, as required by paragraph (g) of this AD, is no 
longer required.

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. Send information to ATTN: Ivan Li, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6437; fax (425) 917-6590. Or, e-mail 
information to [email protected].
    (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 principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (3) AMOCs approved previously in accordance with AD 2006-05-02 
are approved as alternative methods of compliance with the 
corresponding requirements of this AD.
    (4) Accomplishment of the inspections specified in this AD is 
considered an AMOC for the applicable requirements of paragraphs (h) 
and (i) of AD 2004-07-22 R1, Amendment 39-15326, under the 
conditions specified in paragraphs (m)(4)(i) and (m)(4)(ii) of this 
AD.
    (i) The inspections specified in this AD must be done within the 
compliance times specified in AD 2004-07-22 R1. The initial 
inspection specified in this AD must be done at the times specified 
in paragraph (i) of AD 2004-07-22 R1, and the inspections specified 
in this AD must be repeated within the intervals specified in 
paragraph (g) of this AD.
    (ii) The AMOC specified in paragraph (m)(4) of this AD applies 
only to the areas of Boeing Supplemental Structural Inspection 
Document for Model 747 Airplanes, Document D6-35022, Revision G, 
dated December 2000, that are specified in Boeing Alert Service 
Bulletin 747-53A2500, dated December 21, 2004; or Boeing Alert 
Service Bulletin 747-53A2500, Revision 1, dated September 25, 2008.
    (5) 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

    (n) You must use Boeing Alert Service Bulletin 747-53A2500, 
dated December 21, 2004, as of April 6, 2006: or Boeing Alert 
Service Bulletin 747-53A2500, Revision 1, dated September 25, 2008; 
as applicable; 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 Boeing Alert Service Bulletin 747-
53A2500, Revision 1, dated September 25, 2008, under 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The Director of the Federal Register approved the 
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2500, dated December 21, 2004, as of April 6, 2006 (71 FR 10605, 
March 2, 2006).
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
[email protected]; Internet https://www.myboeingfleet.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (5) You may also review copies of the service information that 
is incorporated by reference 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 17, 2009.
Stephen P. Boyd,
Acting Manger, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-30968 Filed 1-11-10; 8:45 am]
BILLING CODE 4910-13-P