[Federal Register Volume 71, Number 152 (Tuesday, August 8, 2006)]
[Proposed Rules]
[Pages 44933-44935]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-12835]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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  Federal Register / Vol. 71 , No. 152 / Tuesday, August 8, 2006 / 
Proposed Rules  

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-22518; Directorate Identifier 2006-NM-092-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100B SUD, 747-200B, 
747-300, 747-400, 747-400D, and 747SP 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 747-100B SUD, 747-200B, 747-300, 747-400, 747-
400D, and 747SP series airplanes. This proposed AD would require 
repetitive inspections for cracking of the crease beam and adjacent 
intercostals, stringers, frames, and skin panels; and related 
investigative and corrective actions if cracking is found. This 
proposed AD results from a report indicating that an operator 
discovered crease beam cracking on two Model 747 airplanes. We are 
proposing this AD to detect and correct cracking of the crease beam and 
adjacent structure, which could become large and result in in-flight 
depressurization and inability of the airframe structure to sustain 
flight loads.

DATES: We must receive comments on this proposed AD by September 22, 
2006.

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: Nicholas Kusz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6432; 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-2006-
22518; Directorate Identifier 2006-NM-092-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 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 an operator discovered 
crease beam cracking due to fatigue on two Model 747 airplanes during 
inspections specified in the 747 Supplemental Structural Inspection 
Document. This condition, if not detected and corrected, could cause 
in-flight depressurization and inability of the structure to sustain 
flight loads.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2591, dated 
April 6, 2006. The service bulletin describes procedures for performing 
repetitive detailed inspections for cracking of the crease beam and 
adjacent intercostals, stringers, frames, and skin panels; and related 
investigative and corrective actions if cracking is found. Related 
investigative actions include performing a surface high-frequency eddy 
current (HFEC) inspection for cracking of the adjacent skin panel 
fastener locations, including all skin fasteners common to the crease 
beam in the areas between the next fuselage frame directly forward and 
aft of the crack location. Corrective actions include repair of any 
crack before further flight. If any crack is outside the limits 
specified in the Boeing 747 Structural Repair Manual, the service 
bulletin specifies to contact the manufacturer for repair data. The 
service bulletin also:
     Describes procedures for submitting a report if any skin 
panel or more than two intercostal webs or skin panel fastener clips 
are found to be cracked;
     Specifies a compliance time of 14,000 total flight cycles 
or 1,500 flight cycles after the date of the service bulletin, 
whichever occurs later; and

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     Specifies an interval of 6,000 flight cycles for 
performing the repetitive inspections.
    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 
``Differences Between the Proposed AD and Service Bulletin.''

Differences Between the Proposed AD and Service Bulletin

    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.
    Although the Accomplishment Instructions of the service bulletin 
describe procedures for submitting certain information to the 
manufacturer, this proposed AD would not require those actions.

Costs of Compliance

    There are about 615 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 65 airplanes of 
U.S. registry. The proposed detailed inspection would take about 8 work 
hours per airplane, per inspection cycle, 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 $41,600, or $640 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.


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-2006-22518; Directorate Identifier 2006-NM-
092-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
22, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100B SUD, 747-200B, 747-
300, 747-400, 747-400D, and 747SP series airplanes, certificated in 
any category; as identified in Boeing Alert Service Bulletin 747-
53A2591, dated April 6, 2006 (referred to after this paragraph as 
``the service bulletin'').

Unsafe Condition

    (d) This AD results from a report indicating that an operator 
discovered crease beam cracking on two Model 747 airplanes. We are 
issuing this AD to detect and correct cracking of the crease beam 
and adjacent structure, which could become large and result in in-
flight depressurization and inability of the airframe structure to 
sustain flight loads.

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.

Repetitive Detailed Inspections and Related Investigative and 
Corrective Actions

    (f) Perform a detailed inspection for cracking of the crease 
beam and adjacent intercostals, stringers, frames, and skin panels 
at the applicable initial and repetitive compliance times specified 
in Table 1 of paragraph 1.E., ``Compliance,'' of the service 
bulletin; except, where the service bulletin specifies an initial 
compliance time after the date on the service bulletin, this AD 
requires compliance within the specified compliance time after the 
effective date of this AD. Do all applicable related investigative 
and corrective actions before further flight if any cracking is 
found. Do all applicable actions in and in accordance with the 
Accomplishment Instructions of the service bulletin, except as 
provided by paragraphs (f)(1) and (f)(2) of this AD.
    (1) Where the service bulletin specifies to contact the 
manufacturer for instructions on how to repair certain conditions, 
before further flight, repair those conditions using a method 
approved in accordance with paragraph (g) of this AD.
    (2) Where the service bulletin specifies to report certain 
information to the manufacturer, this AD does not include that 
requirement.

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) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

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    (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.

    Issued in Renton, Washington, on July 27, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-12835 Filed 8-7-06; 8:45 am]
BILLING CODE 4910-13-P