[Federal Register Volume 70, Number 18 (Friday, January 28, 2005)]
[Proposed Rules]
[Pages 4048-4050]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-1584]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20136; Directorate Identifier 2004-NM-185-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-200B, -200C, -200F, 
and -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 certain Boeing Model 747 series airplanes. This proposed AD would 
require repetitive detailed inspections for cracks in the crease beam 
and adjacent structure of the fuselage, and related investigative and 
corrective actions if necessary. This proposed AD is prompted by 
fatigue cracks found in the crease beam during a follow-on inspection 
of a previously installed modification. We are proposing this AD to 
find and fix fatigue cracking of the fuselage frame, which could result 
in reduced structural integrity of the frame and consequent rapid 
decompression of the airplane.

DATES: We must receive comments on this proposed AD by March 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.

FOR FURTHER INFORMATION CONTACT: Technical Information: Nick Kusz, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6432; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2005-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2005-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

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-2005-20136; 
Directorate Identifier 2004-NM-185-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.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.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

    We have received a report indicating that cracking was found on a 
747-200 series airplane during a follow-on inspection of a previously 
installed modification of the crease beam of the fuselage. The cracking 
is attributed to fatigue due to cabin pressurization cyclic loading. 
This condition, if not corrected, could result in reduced structural 
integrity of the fuselage frame and consequent rapid decompression of 
the airplane.
    The crease beam of the fuselage on certain Model 747-200B, -200C, -
200F, and -400F series airplanes is identical to that on the affected 
Model 747-200 series airplane. Therefore, all of these models may be 
subject to the same unsafe condition.

Other Related Rulemaking

    On October 26, 1989, we issued AD 89-08-03 R1, amendment 39-6389 
(54 FR 46367, November 3, 1989), applicable to certain Boeing Model 747 
series airplanes, (line numbers 66 through 603 inclusive). That AD 
requires inspections for cracks of the fuselage between body station 
(BS) 940 and BS 1000, the body crown crease beam, and the intercostal 
structure; and repair if necessary. The newly reported fatigue cracking 
of the crease beam and adjacent structure of the fuselage that prompted 
this new proposed AD occurred at approximately 10,000 flight

[[Page 4049]]

cycles after the airplane had been modified per the repair procedures 
specified in Boeing Service Bulletin 747-53-2297, Revision 1, dated 
January 26, 1989 (referenced in AD 89-08-03 R1 for accomplishing the 
specified actions).
    Although AD 89-08-03 R1 contains adequate post-modification/repair 
inspections, there are no such inspections required for airplanes with 
line numbers 604 and subsequent. This proposed AD would require 
inspections for airplanes that are not included in the applicability 
specified in AD 89-08-03 R1.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2504, dated 
August 19, 2004. The service bulletin describes procedures for 
repetitive detailed inspections for cracks in the crease beam and 
adjacent structure of the fuselage, and related investigative and 
corrective actions if necessary. The related investigative action is a 
high frequency eddy current inspection for additional cracking in 
adjacent skin panel fastener locations. The corrective action involves 
repairing any cracks found during any inspection. 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 under 
``Differences Between Proposed AD and Service Bulletin.''

Differences Between Proposed AD and Service Bulletin

    For certain airplanes, the service bulletin recommends reporting 
any discrepancies to the manufacturer; however, this proposed AD does 
not include that requirement.
    Although the service bulletin specifies that operators may contact 
the manufacturer for disposition of certain repair conditions, this 
proposed AD would require operators to repair those conditions 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 (DOA) 
Organization whom we have authorized to make those findings.

Costs of Compliance

    There are about 163 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 30 airplanes of 
U.S. registry. The proposed inspection would take about 8 work hours 
per airplane, at an average labor rate of $65 per work hour. Based on 
these figures, the estimated cost of the proposed inspection for U.S. 
operators is $15,600, or $520 per airplane, per inspection cycle.

Authority for This Rulemaking

    The FAA's authority to issue rules regarding aviation safety is 
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated 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 
proposed AD.

Regulatory Findings

    We have determined that this proposed AD will not have federalism 
implications under Executive Order 13132. This proposed 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 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-2005-20136; Directorate Identifier 200--NM-
185-AD.

Comments Due Date

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

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-200B, -200C, -200F, and 
-400F series airplanes, line numbers 604 and subsequent, 
certificated in any category; as listed in Boeing Alert Service 
Bulletin 747-53A2504, dated August 19, 2004.

Unsafe Condition

    (d) This AD was prompted by fatigue cracks found in the crease 
beam during a follow-on inspection of a previously installed 
modification. We are issuing this AD to find and fix fatigue 
cracking of the fuselage frame, which could result in reduced 
structural integrity of the frame and consequent rapid decompression 
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.

Repetitive Inspections

    (f) Accomplish a detailed inspection for cracks in the crease 
beam and adjacent structure of the fuselage by doing all the 
applicable actions in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2504, dated 
August 19, 2004; at the applicable time specified in paragraph 
(f)(1) or (f)(2) of this AD. Repeat the inspection thereafter at 
intervals not to exceed 6,000 flight cycles.
    (1) For Groups 1 and 2 airplanes as identified in the service 
bulletin: Before the accumulation of 10,000 total flight cycles, or 
within 1,500 flight cycles after the effective date of this AD, 
whichever is later.
    (2) For Groups 3 and 4 airplanes as identified in the service 
bulletin: Before the

[[Page 4050]]

accumulation of 14,000 total flight cycles, or within 1,500 flight 
cycles after the effective date of this AD, whichever is later.

Related Investigative and Corrective Actions

    (g) If any crack is found during any inspection required by 
paragraph (f) of this AD: Before further flight, repair the cracking 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2504, dated August 19, 2004. If cracking of 
the crease beam or outer tee chord attachment is found: Before 
further flight, do a high frequency eddy current inspection for 
additional cracking, and repair any cracking found, in accordance 
with the service bulletin. Where the service bulletin specifies 
contacting the manufacturer for disposition of certain repair 
conditions, repair before further flight in accordance with a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or by an Authorized Representative for the Boeing 
Delegation Option Authorization (DOA) 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.

No Reporting Required

    (h) For certain airplanes, the service bulletin referenced in 
this AD recommends reporting any discrepancies to the manufacturer, 
but this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle ACO, 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 a repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing DOA Organization who has 
been authorized by the Manager, Seattle ACO, to make such findings.

    Issued in Renton, Washington, on January 18, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-1584 Filed 1-27-05; 8:45 am]
BILLING CODE 4910-13-P