Airworthiness Directives; Boeing Model 747-100, -200B, -200C, and -200F Series Airplanes, 49161-49162 [E7-16420]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 72, Number 166 (Tuesday, August 28, 2007)]
[Rules and Regulations]
[Pages 49161-49162]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-16420]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28257; Directorate Identifier 2007-NM-034-AD; 
Amendment 39-15171; AD 2007-17-13]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -200B, -200C, and 
-200F Series Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 747-100, -200B, -200C, and -200F series airplanes. 
This AD requires performing repetitive inspections for cracks in the 
fuselage skin at the cutout of the bulk cargo door light, and 
corrective actions if necessary. This AD also provides terminating 
action for airplanes with a certain type of damage. This AD results 
from a report of a 2-inch crack through the fuselage skin and internal 
bonded doubler at the cutout of the bulk cargo door light. We are 
issuing this AD to detect and correct cracks in the fuselage skin at 
the cutout of the bulk cargo door light, which could result in reduced 
structural integrity of the fuselage at the bulk cargo door and 
consequent rapid decompression of the fuselage.

DATES: This AD becomes effective October 2, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of October 2, 
2007.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue, SE., Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

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:

Examining the Docket

    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in person at the Docket Operations office between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The Docket Operations 
office (telephone (800) 647-5527) is located on the ground floor of the 
West Building at the DOT street address stated in the ADDRESSES 
section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Boeing Model 
747-100, -200B, -200C, and -200F series airplanes. That NPRM was 
published in the Federal Register on May 24, 2007 (72 FR 29084). That 
NPRM proposed to require performing repetitive inspections for cracks 
in the fuselage skin at the cutout of the bulk cargo door light, and 
corrective actions if necessary. That NPRM also proposed to provide 
terminating action for airplanes with a certain type of damage.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received. The 
commenter, Boeing, supports the NPRM.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    There are about 65 airplanes of the affected design in the 
worldwide fleet. This AD affects about 36 airplanes of U.S. registry. 
The required actions take about 2 work hours per airplane, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the AD for U.S. operators is $5,760, or $160 per 
airplane, per inspection cycle.

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

[[Page 49162]]

by adding the following new airworthiness directive (AD):

2007-17-13 Boeing: Amendment 39-15171. Docket No. FAA-2007-28257; 
Directorate Identifier 2007-NM-034-AD.

Effective Date

    (a) This AD becomes effective October 2, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, -200B, -200C, and -
200F series airplanes, certificated in any category; as identified 
in Boeing Alert Service Bulletin 747-53A2673, dated February 8, 
2007.

Unsafe Condition

    (d) This AD results from a report of a 2-inch crack through the 
fuselage skin and internal bonded doubler at the cutout of the bulk 
cargo door light. We are issuing this AD to detect and correct 
cracks in the fuselage skin at the cutout of the bulk cargo door 
light, which could result in reduced structural integrity of the 
fuselage at the bulk cargo door and consequent rapid decompression 
of the fuselage.

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/Corrective Actions

    (f) Before the accumulation of 20,000 total flight cycles, or 
within 1,500 flight cycles after the effective date of this AD, 
whichever is later: Perform a high frequency eddy current (HFEC) 
inspection for cracks in the fuselage skin at the cutout of the bulk 
cargo door light, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2673, dated February 8, 
2007. Repeat the inspection thereafter at intervals not to exceed 
3,000 flight cycles.
    (1) If no crack is found: Repeat the inspection required by 
paragraph (f) of this AD at the time specified.
    (2) If any crack is found that is 2.0 inches or less in length 
from the edge of the light cutout forward lower corner: Before 
further flight, do all the corrective actions (including an 
additional HFEC inspection for cracks) in accordance with Part 2 of 
the Accomplishment Instructions of the service bulletin. 
Accomplishing the actions specified in Part 2 of the service 
bulletin ends the repetitive inspections required by paragraph (f) 
of this AD.
    (3) If any crack is found during the inspection required by 
paragraph (f) of this AD that is more than 2.0 inches in total 
length from the edge of the light cutout forward lower corner, or is 
at a location other than the light cutout forward lower corner: 
Before further flight, repair using a method approved in accordance 
with the procedures specified in paragraph (g)(2) of this AD.

Alternative Methods of Compliance (AMOCs)

    (g)(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) 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.
    (3) 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.

Material Incorporated by Reference

    (h) You must use Boeing Alert Service Bulletin 747-53A2673, 
dated February 8, 2007, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies 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: 
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 14, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-16420 Filed 8-27-07; 8:45 am]
BILLING CODE 4910-13-P