Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP Series Airplanes

[Federal Register Volume 74, Number 49 (Monday, March 16, 2009)]
[Rules and Regulations]
[Pages 11013-11014]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-4973]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1072; Directorate Identifier 2008-NM-109-AD; 
Amendment 39-15838; AD 2009-06-02]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 
747SP 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 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
200F, 747-300, 747-400, 747SR, and 747SP series airplanes. This AD 
requires inspecting for skin cracks at the shear tie end fastener 
locations of the fuselage frames, and repairing cracks if necessary. 
This AD results from a wide-spread fatigue damage assessment of Model 
747 airplanes. We are issuing this AD to detect and correct cracks in 
the fuselage skin that can propagate and grow, resulting in a loss of 
structural integrity and a sudden decompression of the airplane during 
flight.

DATES: This AD is effective April 20, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 20, 
2009.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207; telephone 206-544-9990; fax 206-766-5682; 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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
certain Boeing model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747-400, 747SR, and 747SP series airplanes. 
That NPRM was published in the Federal Register on October 8, 2008 (73 
FR 58901). That NPRM proposed to require inspecting for skin cracks at 
the shear tie end fastener locations of the fuselage frames, and 
repairing cracks if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Boeing concurs with the 
contents of the NPRM.

Conclusion

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

Costs of Compliance

    We estimate that this AD affects 147 airplanes of U.S. registry. We 
also estimate that it takes 30 work-hours for the detailed inspection, 
or 49 work hours for the HFEC inspection, per product, to comply with 
this AD. The average labor rate is $80 per work-hour. Based on these 
figures, we estimate the cost of this AD to the U.S. operators to be 
$352,800 or $576,240, or $2,400 or $3,920 per product.

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

[[Page 11014]]

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:

2009-06-02 Boeing: Amendment 39-15838. Docket No. FAA-2008-1072; 
Directorate Identifier 2008-NM-109-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective April 20, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 
747SP series airplanes, certificated in any category; as identified 
in Boeing Alert Service Bulletin 747-53A2682, dated May 8, 2008.

Unsafe Condition

    (d) This AD results from a wide-spread fatigue damage assessment 
of Model 747 airplanes. We are issuing this AD to detect and correct 
cracks in the fuselage skin that can propagate and grow, resulting 
in a loss of structural integrity and sudden decompression of the 
airplane during flight.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.

Inspections/Repair

    (f) Except as provided by paragraphs (g) and (h) of this AD: At 
the applicable compliance times specified in paragraph 1.E. of 
Boeing Alert Service Bulletin 747-53A2682, dated May 8, 2008 (``the 
service bulletin''), do an external detailed inspection or external 
high frequency eddy current inspection for skin cracks at the shear 
tie end fastener locations of the fuselage frames, and repair any 
skin cracks before further flight, by accomplishing all of the 
applicable actions specified in the Accomplishment Instructions of 
the service bulletin. Repeat the applicable inspection thereafter at 
the applicable interval specified in paragraph 1.E. of the service 
bulletin.

Exceptions to the Service Bulletin

    (g) Where paragraph 1.E. of Boeing Alert Service Bulletin 747-
53A2682, dated May 8, 2008, specifies counting the compliance time 
from ``* * * the date on this service bulletin,'' this AD requires 
counting the compliance time from the effective date of this AD.
    (h) If any crack is found in a structural repair manual skin 
repair during any inspection required by paragraph (f) of this AD, 
and Boeing Alert Service Bulletin 747-53A2682, dated May 8, 2008, 
specifies to contact Boeing for repair: Before further flight, 
repair using a method approved in accordance with the procedures 
specified in paragraph (i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office (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.
    (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) 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

    (j) You must use Boeing Alert Service Bulletin 747-53A2682, 
dated May 8, 2008, 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; telephone 206-544-9990; fax 206-766-5682; e-mail 
[email protected]; Internet https://www.myboeingfleet.com.
    (3) 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.
    (4) 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 February 27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-4973 Filed 3-13-09; 8:45 am]
BILLING CODE 4910-13-P

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