[Federal Register Volume 70, Number 68 (Monday, April 11, 2005)]
[Proposed Rules]
[Pages 18332-18335]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-7155]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20880; Directorate Identifier 2003-NM-229-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, 
-200B, and -300 Series Airplanes; and Model 747SP and 747SR 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 supersede an existing airworthiness 
directive (AD) for certain Boeing Model 747 series airplanes. That AD 
currently requires repetitive inspections to detect cracks in various 
areas of the fuselage

[[Page 18333]]

internal structure, and repair if necessary. This proposed AD would 
require repetitive inspections of additional areas of the fuselage 
internal structure, and related investigative/corrective actions if 
necessary. This proposed AD also would remove certain requirements from 
the existing AD. This proposed AD is prompted by the results of fatigue 
testing of the fuselage structure of a Boeing Model 747SR series 
airplane. We are proposing this AD to prevent the 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 May 26, 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.
     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 Airplane Group, 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-2005-20880; the directorate identifier for this docket is 
2003-NM-229-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-2005-20880; 
Directorate Identifier 2003-NM-229-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 our 
docket 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 the 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 can examine the AD docket 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

    On May 14, 2002, we issued AD 2002-10-10, amendment 39-12756 (67 FR 
36081, May 23, 2002), for certain Boeing Model 747 series airplanes. 
That AD requires repetitive inspections to detect cracking in various 
areas of the fuselage internal structure, and repair if necessary. That 
AD was prompted by the results of fatigue testing that revealed severed 
upper chords of the upper deck floor beams due to fatigue cracking. We 
issued that AD to prevent loss of the structural integrity of the 
fuselage, which could result in rapid depressurization of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2002-10-10, the manufacturer reported that 
cracking was found on the fatigue test airplane in areas not included 
in Boeing Service Bulletin 747-53-2349, dated June 27, 1991; or Boeing 
Alert Service Bulletin 747-53A2349, Revision 1, dated October 12, 2000. 
(Those service bulletins were referenced as the appropriate sources of 
service information in AD 2002-10-10.) The new areas are the fuselage 
skin at all four corners of the main electronics bay access door 
cutout, and certain nose wheel well (NWW) sidewall panels and 
stiffeners, and certain main deck floor beams at the NWW vertical 
beams.

Relevant Service Information

    We have reviewed Boeing Service Bulletin 747-53A2349, Revision 2, 
dated April 3, 2003. The service bulletin describes procedures that are 
essentially the same as the procedures in Boeing Alert Service Bulletin 
747-53A2349, Revision 1. Revision 2 includes a new inspection area, 
Area 9. Area 9 includes the fuselage skin at all four corners of the 
main electronics bay access door cutout. Revision 2 also includes 
additional inspections in Area 7. Area 7 now includes certain NWW 
sidewall panels and stiffeners between STA 340 and STA 400, and the STA 
360 and 380 main deck floor beams at the NWW vertical beams. The 
actions described in Revision 2 also affect Area 1. Among other things, 
for Group 3 airplanes only, Area 1 has also been redefined.
    For airplanes on which any cracking is found, Revision 2 references 
the Boeing 747 Structural Repair Manual for repair instructions. For 
airplanes with damage that is beyond the limits specified in the 
service bulletin, the service bulletin specifies contacting Boeing for 
repair data.

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 products 
of this same type design. Therefore, we are proposing this AD, which 
would supersede AD 2002-10-10. This proposed AD would continue to 
require repetitive inspections to detect cracks in various areas of the 
fuselage internal structure, and repair if necessary. This proposed AD 
would also require repetitive inspections of additional areas of the 
fuselage internal structure, and related investigative/corrective 
actions if necessary. This proposed AD also would remove all 
requirements related to the upper deck floor beams from the existing 
AD, as discussed below under ``Other Related Rulemaking.'' This 
proposed AD would require you to use the service information described 
previously to perform these actions, except as discussed under 
``Differences Between

[[Page 18334]]

the Proposed AD and Service Information.''

Other Related Rulemaking

    Operators should note that we plan to issue a separate AD 
rulemaking action (reference Directorate Identifier 2004-NM-55-AD) to 
address the identified unsafe condition as it relates to the upper deck 
floor beams. Therefore, all requirements from AD 2002-10-10 that relate 
to the upper deck floor beams are in that separate AD rulemaking 
action.

Differences Between the Proposed AD and Service Information

    The service bulletin specifies that you may contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require you to repair 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 Delegation Option Authorization Organization whom we 
have authorized to make those findings.

Change to Existing AD

    This proposed AD would retain certain requirements of AD 2002-10-
10. Since AD 2002-10-10 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
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                                          Corresponding  requirement in
     Requirement in AD 2002-10-10               this proposed AD
------------------------------------------------------------------------
Paragraph (a).........................  Paragraph (f).
Paragraph (b).........................  Paragraph (g).
Paragraph (c).........................  Paragraph (h).
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Costs of Compliance

    This proposed AD would affect about 489 airplanes worldwide, and 
155 airplanes of U.S. registry. The following table provides the 
estimated costs for U.S. operators to comply with this proposed AD.

                                                 Estimated Costs
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                                                                             Cost per
                                               Average                      airplane,    Number  of
            Action              Work  hours  labor  rate       Parts           per          U.S.      Fleet cost
                                              per  hour                     inspection   registered
                                                                              cycle      airplanes
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Inspections, excluding upper            145          $65  None...........       $9,425          155   $1,460,875
 deck floor beams, per
 inspection cycle (required by
 AD 2002-10-10).
Inspections (new proposed AD).          130           65  None...........        8,450          155    1,309,750
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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 removing amendment 39-12756 (67 FR 
36081, May 23, 2002) and adding the following new airworthiness 
directive (AD):

Boeing: Docket No. FAA-2005-20880; Directorate Identifier 2003-NM-
229-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this airworthiness directive (AD) action by May 26, 2005.

Affected ADs

    (b) This AD supersedes AD 2002-10-10, amendment 39-12756 (67 FR 
36081, May 23, 2002).

Applicability

    (c) This AD applies to Boeing Model 747-100, -100B, -100B SUD, -
200B, and -300 series airplanes; and Model 747SP and 747SR series 
airplanes; certificated in any category; identified in Boeing 
Service Bulletin 747-53A2349, Revision 2, dated April 3, 2003.

Unsafe Condition

    (d) This AD was prompted by the results of fatigue testing of 
the fuselage structure of a Boeing Model 747SR series airplane. We 
are issuing this AD to prevent the 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

[[Page 18335]]

the compliance times specified, unless the actions have already been 
done.

Restatement of Requirements of AD 2002-10-10 (Excluding Upper Deck 
Floor Beams)

Repetitive Inspections

    (f) Prior to the accumulation of 22,000 total flight cycles, or 
within 1,000 flight cycles after June 11, 1993 (the effective date 
of AD 93-08-12, amendment 39-8559), whichever occurs later, unless 
accomplished previously within the last 2,000 flight cycles; and 
thereafter at intervals not to exceed 3,000 flight cycles: Perform 
an internal detailed inspection to detect cracks in the areas of the 
fuselage internal structure specified in paragraphs (f)(1) through 
(f)(6) of this AD; in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; or Boeing Service 
Bulletin 747-53A2349, Revision 2, dated April 3, 2003. After the 
effective date of this AD, only Revision 2 of Boeing Service 
Bulletin 747-53A2349 may be used. Continue doing the inspections 
until the inspections required by paragraph (i) of this AD are done.
    (1) Section 42 upper lobe frames.
    (2) Section 46 lower lobe frames.
    (3) Section 42 lower lobe frames.
    (4) Main entry door cutouts.
    (5) Section 41 body station 260, 340, and 400 bulkheads.
    (6) Main entry doors.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

    (g) Prior to the accumulation of 25,000 total flight cycles, or 
within 1,000 flight cycles after June 11, 1993, whichever is later, 
unless already done within the last 2,000 flight cycles; and 
thereafter at intervals not to exceed 3,000 flight cycles: Do an 
internal detailed inspection to detect cracks in the Section 46 
upper lobe frames, in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; or Boeing Service 
Bulletin 747-53A2349, Revision 2, dated April 3, 2003. After the 
effective date of this AD, only Revision 2 of Boeing Service 
Bulletin 747-53A2349 may be used.

Repair

    (h) Before further flight, repair any cracks detected during the 
inspections done per paragraph (f) or (g) of this AD, in accordance 
with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA; or according to data meeting the 
certification basis of the airplane approved a Boeing Company 
Designated Engineering Representative (DER) who has been authorized 
by the Manager, Seattle ACO, to make such findings; or by an 
Authorized Representative (AR) 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 approval must specifically reference this AD.

New Requirements of This AD

Repetitive Inspections

    (i) Do an internal detailed inspection to detect cracking in the 
areas of the fuselage internal structure specified in paragraphs 
(i)(1), (i)(2), (i)(3), and (i)(5) of this AD, and internal and 
external detailed inspections of the areas specified in paragraphs 
(i)(4), (i)(6), and (i)(7) of this AD. Do the inspections in 
accordance with Boeing Service Bulletin 747-53A2349, Revision 2, 
dated April 3, 2003. Do the inspections at the applicable time 
specified in paragraph (j) of this AD. Accomplishment of these 
inspections terminates the requirements of paragraph (f) of this AD.
    (1) Section 42 upper lobe frames.
    (2) Section 46 lower lobe frames.
    (3) Section 42 lower lobe frames.
    (4) Main entry door cutouts.
    (5) Nose wheel well bulkheads, sidewall panels, and the STA 360 
and 380 floor beams. These areas include the Section 41 body station 
260, 340, and 400 bulkheads.
    (6) Main entry doors.
    (7) Main electronics bay access door cutout.
    (j) Do the inspections required by paragraph (i) of this AD at 
the applicable time specified in paragraph (j)(1), (j)(2), or (j)(3) 
of this AD. Repeat the inspections thereafter at intervals not to 
exceed 3,000 flight cycles.
    (1) For airplanes on which the inspections required by 
paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(6) of this AD 
have been done before the effective date of this AD, but the 
inspections required by paragraphs (i)(5) and (i)(7) of this AD have 
not been done: Within 3,000 flight cycles since accomplishment of 
the most recent inspection required by paragraphs (f)(1), (f)(2), 
(f)(3), (f)(4), and (f)(6) of this AD.
    (2) For airplanes on which the inspections required by 
paragraphs (i)(5) and (i)(7) have been done before the effective 
date of this AD: Within 3,000 flight cycles since accomplishment of 
the most recent inspection required by paragraphs (i)(5) and (i)(7) 
of this AD, or within 1,000 flight cycles after the effective date 
of this AD, whichever is later.
    (3) For airplanes on which the inspections required by paragraph 
(f) of this AD have not been done before the effective date of this 
AD: Prior to the accumulation of 22,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever is later.

Repair

    (k) Before further flight, repair any cracking found during any 
inspection required by paragraph (i) of this AD in accordance with 
Boeing Service Bulletin 747-53A2349, Revision 2, dated April 3, 
2003. Where the service bulletin specifies to contact Boeing for 
repair instructions, repair in accordance with a method approved by 
the Manager, Seattle ACO; or in accordance with data meeting the 
type certification basis of the airplane, and that have been 
approved by an AR for the Boeing DOA who has been authorized by the 
FAA to make those findings. For a repair method to be approved by 
the Manager, Seattle ACO, as required by this paragraph, the 
approval letter must specifically reference this AD.

Actions Previously Accomplished

    (l) Inspections required by paragraph (i) of this AD, 
accomplished before the effective date of this AD, in accordance 
with the Accomplishment Instructions of Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; or Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; are acceptable for 
compliance with the corresponding action required by paragraph (i) 
of this AD.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19.
    (2) Alternative methods of compliance and FAA-approved repairs, 
approved previously in accordance with AD 2002-10-10 or AD 93-08-12, 
are approved as alternative methods of compliance with the 
corresponding requirements of this AD.


    Issued in Renton, Washington, on April 1, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7155 Filed 4-8-05; 8:45 am]
BILLING CODE 4910-13-P