[Federal Register Volume 72, Number 100 (Thursday, May 24, 2007)]
[Proposed Rules]
[Pages 29084-29086]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-10045]


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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]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 747-100, -200B, -200C, and -200F series 
airplanes. This proposed AD would require performing repetitive 
inspections for cracks in the fuselage skin at the cutout of the bulk 
cargo door light, and corrective actions if necessary. This proposed AD 
also provides terminating action for airplanes with a certain type of 
damage. This proposed 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 proposing 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: We must receive comments on this proposed AD by July 9, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed 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:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
28257; Directorate Identifier 2007-NM-034-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that web site, anyone can find and read the

[[Page 29085]]

comments in any of our dockets, including the name of the individual 
who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You may review DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

    You may 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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    We have received a report indicating that a 2-inch crack through 
the fuselage skin and internal bonded doubler at the cutout of the bulk 
cargo door light was found during a visual fuselage skin inspection on 
a Model 747-200F series airplane. The crack was located at the forward 
lower corner of the cutout of the bulk cargo door light between 
stations 2060 and 2070, stringers 32R and 33R. The airplane had 
accumulated approximately 24,613 flight cycles and 99,339 flight hours. 
This condition, if not corrected, could result in reduced structural 
integrity of the fuselage at the bulk cargo door and consequent rapid 
decompression of the fuselage.
    The subject area on certain Model 747-100, 200B, and -200C series 
airplanes is almost identical to that on the affected Model 747-200F 
series airplanes. Therefore, those airplanes are subject to the unsafe 
condition revealed on the Model 747-200F series airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2673, dated 
February 8, 2007. The service bulletin describes procedures for 
repetitive high frequency eddy current (HFEC) inspections for cracks in 
the fuselage skin at the cutout of the bulk cargo door light, and 
corrective actions if necessary. The corrective actions are as follows:
     For airplanes on which a crack is found that is 2.0 inches 
or less in length from the edge of the light cutout forward lower 
corner, Part 2 of the Accomplishment Instructions of the service 
bulletin describes procedures for installing a repair filler, doubler, 
and tripler, and performing an additional HFEC inspection of the trim 
edge for cracks and repairing any crack. Accomplishing these corrective 
actions eliminates the need for the repetitive inspections.
     For airplanes on which a crack is found 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, the service bulletin recommends contacting Boeing for 
repair instructions and doing the repair.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Difference Between the Proposed AD and Service Information.''

Difference Between the Proposed AD and Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.

Costs of Compliance

    There are about 65 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 36 airplanes of 
U.S. registry. The proposed actions would 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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

[[Page 29086]]

Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2007-28257; Directorate Identifier 2007-NM-
034-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 9, 
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 Part 2 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.

    Issued in Renton, Washington, on May 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-10045 Filed 5-23-07; 8:45 am]
BILLING CODE 4910-13-P