[Federal Register Volume 70, Number 188 (Thursday, September 29, 2005)]
[Proposed Rules]
[Pages 56860-56862]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-19239]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22526; Directorate Identifier 2005-NM-008-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-200F, 747-200C, 747-
400, 747-400D, and 747-400F 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 all Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-
400F series airplanes. This proposed AD would require repetitive 
inspections for cracking of certain fuselage internal structure, and 
repair if necessary. This proposed AD is prompted by fatigue tests and 
analysis that identified areas of the fuselage where fatigue cracks can 
occur. We are proposing this AD to prevent loss of the structural 
integrity of the fuselage, which could result in rapid depressurization 
of the airplane.

DATES: We must receive comments on this proposed AD by November 14, 
2005.

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.
     By 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.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-22526; the directorate identifier for this docket is 
2005-NM-008-AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; 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 under ADDRESSES. Include ``Docket No. FAA-2005-22526; 
Directorate Identifier 2005-NM-008-AD'' in the subject line 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 submitted 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 can review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can 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 DMS receives them.

Discussion

    Boeing has completed extended pressure fatigue tests on a Boeing 
Model 747SR and a 747-400 fuselage test article. Boeing has also used 
updated analysis methods on the 747 fuselage structure. The tests and 
analysis have identified areas of the fuselage where fatigue cracks can 
occur. This condition, if not corrected, could result in loss of the 
structural integrity of the fuselage and consequent rapid 
depressurization of the airplane.

Related AD

    On May 14, 2002, we issued AD 2002-10-10, amendment 39-12756 (67 FR 
36081, May 23, 2002). That AD applies to certain Boeing Model 747 
airplanes. That AD requires repetitive inspections to detect cracks in 
various areas of the fuselage internal structure, and repair if 
necessary. This proposed AD would require similar inspections for Model 
747 airplanes that are not identified in the applicability of AD 2002-
10-10.
    We also issued AD 2004-07-22, amendment 39-13566 (69 FR 18250, 
April 7, 2004), as corrected (69 FR 19618, April 13, 2005), and as 
further corrected (69 FR 24063, May 3, 2005). That AD applies to all 
Boeing Model 747 series airplanes and requires that the FAA-approved 
maintenance inspection program be revised to include inspections that 
will give no less than the required damage tolerance rating for each 
structural significant item, and repair of cracked structure.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2500, dated 
December 21, 2004. Procedures for repetitive inspections for cracks are 
listed in the following table:

[[Page 56861]]



                       Service Bulletin Procedures
------------------------------------------------------------------------
     The service bulletin describes
            procedures for--                         Of the--
------------------------------------------------------------------------
Internal detailed inspections..........  Upper deck floor beams;
                                         Section 42 frames;
                                         Section 46 frames; and
                                         Nose wheel well bulkheads,
                                          sidewall panels, and the STA
                                          360 and 380 main deck floor
                                          beams.
Internal and external detailed           Main entry doors and door
 inspections.                             cutouts; and
                                         Fuselage skin at all four
                                          corners of the main
                                          electronics bay access door
                                          cutout.
------------------------------------------------------------------------

    The compliance threshold is 22,000 or 25,000 total flight cycles 
(depending on the inspection area and airplane configuration), with a 
repetitive interval of 3,000 flight cycles. The service bulletin 
recommends repairing cracks by using the structural repair manual (SRM) 
or contacting Boeing. 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. Therefore, we are proposing this AD, which 
would require accomplishing the actions specified in the service 
information described previously, except as discussed below.

Differences Between the Proposed AD and the Service Bulletin

    The service bulletin specifies compliance times relative to the 
date of issuance of the service bulletin; however, this proposed AD 
would require compliance before the specified compliance times relative 
to the effective date of this AD.
    Also, the service bulletin specifies contacting the manufacturer 
for instructions on how to repair certain conditions, but this proposed 
AD would require you to repair those conditions by 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 Delegation Option Authorization Organization whom we 
have authorized to make those findings.

Costs of Compliance

    There are about 706 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                                     Estimated Costs
                                                                 (per inspection cycle)
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                    Action                       Work    Average labor                Parts                  Cost per       registered      Fleet cost
                                                hours    rate per hour                                       airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections..................................      260             $65  None required...................         $16,900             107      $1,808,300
--------------------------------------------------------------------------------------------------------------------------------------------------------

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. 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 FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Boeing: Docket No. FAA-2005-22526; Directorate Identifier 2005-NM-
008-AD.

[[Page 56862]]

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by November 14, 2005.

Affected ADs

    (b) Inspections specified in this AD may be considered an 
alternative method of compliance (AMOC) for certain requirements of 
AD 2004-07-22, as specified in paragraph (i)(2) of this AD.

Applicability

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

Unsafe Condition

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

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

    (f) Except as required/provided by paragraphs (g) and (h) of 
this AD: 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. Do the initial and repetitive 
inspections at the times specified in paragraph 1.E. of the service 
bulletin. Repair any crack before further flight after detection.

Exceptions to Service Bulletin Procedures

    (g) If any crack is found during any inspection required by this 
AD, and the bulletin specifies to contact Boeing for appropriate 
action: Before further flight, repair the crack according to a 
method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA; or according to data meeting the certification 
basis of the airplane approved by an Authorized Representative for 
the Boeing 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 reference this AD.
    (h) Where the service bulletin specifies a compliance time after 
the issuance of the service bulletin, this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.

AMOCs

    (i)(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) Accomplishment of the inspections specified in this AD is 
considered an AMOC for the applicable requirements of paragraphs (c) 
and (d) of AD 2004-07-22, amendment 39-13566, under the following 
conditions:
    (i) The actions must be done within the compliance times 
specified in AD 2004-07-22. The initial inspection must be done at 
the times specified in paragraph (d) of AD 2004-07-22, and the 
inspections must be repeated within the intervals specified in 
paragraph (f) of this AD.
    (ii) The AMOC applies only to the areas of Supplemental 
Structural Inspection Document D6-35022, Revision G, that are 
specified in Boeing Alert Service Bulletin 747-53A2500, dated 
December 21, 2004.
    (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 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.
    (4) 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.

    Issued in Renton, Washington, on September 16, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-19239 Filed 9-28-05; 8:45 am]
BILLING CODE 4910-13-P