Document ID: FAA-2009-0636-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Boeing Model 747-100B SUD, -200B, -300, -400, and -400D Series Airplanes
Posted Date: 2009-07-14T04:00Z

[Federal Register Volume 74, Number 133 (Tuesday, July 14, 2009)]
[Proposed Rules]
[Pages 33928-33930]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-16575]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0636; Directorate Identifier 2009-NM-031-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-100B SUD, -200B, -300, 
-400, and -400D 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) that applies to certain Boeing Model 747-100B SUD, -
200B, -300, -400, and -400D series airplanes. The existing AD currently 
requires repetitive inspections for cracking in fuselage stringers 8L, 
8R, 10L, and 10R at body stations 460, 480, and 500 frame locations; 
and repair if necessary. This proposed AD would revise the 
applicability to include an additional airplane, and reduce compliance 
times for the initial inspection and repetitive intervals for Model 
747-400 series airplanes that have been converted to the large cargo 
freighter configuration. This proposed AD results from findings of 
cracking in fuselage stringers 8L, 8R, 10L, and 10R at body stations 
460, 480, and 500 frame locations. We are proposing this AD to detect 
and correct fatigue cracking in certain fuselage stringers, which, if 
left undetected, could result in fuselage skin cracking that reduces 
the structural integrity of the skin panel, and consequent rapid 
depressurization of the airplane.

DATES: We must receive comments on this proposed AD by August 28, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, 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, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221 or 
425-227-1152.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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 send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0636; 
Directorate Identifier 2009-NM-031-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On July 13, 2005, we issued AD 2005-15-08, amendment 39-14197 (70 
FR 43020, July 26, 2005), for certain Boeing Model 747-100B SUD, -200B, 
-300, -400, and -400D series airplanes. That

[[Page 33929]]

AD requires repetitive inspections for cracking in fuselage stringers 
8L, 8R, 10L, and 10R at body stations 460, 480, and 500 frame 
locations; and repair if necessary. That AD resulted from findings of 
cracking in fuselage stringers 8L, 8R, 10L, and 10R at body stations 
460, 480, and 500 frame locations. We issued that AD to detect and 
correct fatigue cracking in certain fuselage stringers, which, if left 
undetected, could result in fuselage skin cracking that reduces the 
structural integrity of the skin panel, and consequent rapid 
depressurization of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2005-15-08, Boeing has revised the service 
information cited in that AD. AD 2005-15-08 cited Boeing Alert Service 
Bulletin 747-53A2484, dated June 26, 2003, as the source of service 
information for the required and optional actions. Revision 1, dated 
February 12, 2009, adds airplane variable number RS699 to the airplane 
effectivity; that variable number was inadvertently omitted from Boeing 
Alert Service Bulletin 747-53A2484, dated June 26, 2003. Also, Model 
747-400 series airplanes that have been converted to the large cargo 
freighter (LCF) configuration (i.e., variable numbers RT631 and RT632) 
have been moved from Group 3 to a new Group 4 with reduced compliance 
times for the initial and repetitive inspections, and have revised 
access instructions due to a different interior configuration. 
Procedures are otherwise unchanged.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2005-15-08 and would continue to require repetitive 
inspections for fatigue cracking in fuselage stringers 8L, 8R, 10L, and 
10R at body station 460, 480, and 500 frame locations; and repair if 
necessary. This proposed AD would also revise the applicability to 
include an additional airplane, and reduce compliance times for initial 
inspection and repetitive interval for Model 747-400 series airplanes 
that have been converted to the large cargo freighter configuration.

Change to Existing AD

    This proposed AD would retain certain requirements of AD 2005-15-
08. Since AD 2005-15-08 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
       Requirement in AD 2005-15-08             in this  proposed AD
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paragraph (d).............................  paragraph (e).
paragraph (e).............................  paragraph (f).
paragraph (f).............................  paragraph (g).
paragraph (g).............................  paragraph (k).
paragraph (h).............................  paragraph (l).
paragraph (i).............................  paragraph (m).
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Costs of Compliance

    There are about 246 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
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                                                                                           Number of U.S.-
              Action                  Work hours     Average labor    Cost per airplane      registered                      Fleet cost
                                                     rate per hour                            airplanes
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Inspection (required by AD 2005-15-              3             $80  $240 per inspection                69  $16,560 per inspection cycle.
 08).                                                                cycle.
Inspection (proposed).............               3              80  $240 per inspection                70  $16,800 per inspection cycle.
                                                                     cycle.
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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 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, Incorporation by 
reference, 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 39-14197 (70 FR

[[Page 33930]]

43020, July 26, 2005) and adding the following new AD:

Boeing: Docket No. FAA-2009-0636; Directorate Identifier 2009-NM-
031-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by August 
28, 2009.

Affected ADs

    (b) This AD supersedes AD 2005-15-08.

Applicability

    (c) This AD applies to Boeing Model 747-100B SUD, -200B, -300, -
400, and -400D series airplanes, certificated in any category; as 
identified in Boeing Service Bulletin 747-53A2484, Revision 1, dated 
February 12, 2009.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from findings of cracking in fuselage 
stringers 8L, 8R, 10L, and 10R at body station 460, 480, and 500 
frame locations. We are issuing this AD to detect and correct 
fatigue cracking in the specified fuselage stringers, which, if left 
undetected, could result in fuselage skin cracking that reduces the 
structural integrity of the skin panel, and consequent rapid 
depressurization of the airplane.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2005-15-08

Inspection for Certain Airplanes Subject to AD 2005-15-08 With New 
Service Bulletin

    (g) For airplanes identified in Boeing Alert Service Bulletin 
747-53A2484, dated June 26, 2003, except airplanes identified in 
paragraph (j) of this AD, do a detailed inspection for cracking in 
fuselage stringers 8L, 8R, 10L, and 10R at body station 460, 480, 
and 500 frame locations, in accordance with Part 1 of the 
Accomplishment Instructions in Boeing Alert Service Bulletin 747-
53A2484, dated June 26, 2003; or Boeing Service Bulletin 747-
53A2484, Revision 1, dated February 12, 2009. Do the inspections at 
the applicable time specified in paragraph (g)(1) or (g)(2) of this 
AD. Repeat the inspection thereafter at intervals not to exceed 
3,000 flight cycles until the requirements of paragraph (l) of this 
AD are accomplished. After the effective date of this AD, use only 
Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 
2009.
    (1) For airplanes with 19,000 total flight cycles or less as of 
August 30, 2005 (the effective date of AD 2005-15-08): Prior to the 
accumulation of 8,000 total flight cycles, or within 2,000 flight 
cycles after August 30, 2005, whichever is later, not to exceed 
20,000 total flight cycles.
    (2) For airplanes with more than 19,000 total flight cycles as 
of August 30, 2005: Within 1,000 flight cycles after August 30, 
2005.

    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.''

New Requirements of This Ad

Inspection: Variable Number RS699

    (h) For Model 747 airplane variable number RS699, do a detailed 
inspection for cracking in fuselage stringers 8L, 8R, 10L, and 10R 
at body station 460, 480, and 500 frame locations, in accordance 
with Boeing Service Bulletin 747-53A2484, Revision 1, dated February 
12, 2009, at the later of the times specified in paragraphs (h)(1) 
and (h)(2) of this AD.
    (1) Before the accumulation of 8,000 total flight cycles.
    (2) Within 2,000 flight cycles after the effective date of this 
AD.
    (i) For Model 747 airplane variable number RS699, repeat the 
inspection specified in paragraph (h) of this AD thereafter at 
intervals not to exceed 3,000 flight cycles until the actions 
specified in paragraph (k) or (l) of this AD are accomplished.

Inspection: Group 4 Airplanes

    (j) For Group 4 airplanes as identified in Boeing Service 
Bulletin 747-53A2484, Revision 1, dated February 12, 2009, do a 
detailed inspection for cracking in fuselage stringers 8L, 8R, 10L, 
and 10R at body station 460, 480, and 500 frame locations, within 
1,000 flight cycles after the effective date of this AD. Do the 
actions in accordance with Boeing Service Bulletin 747-53A2484, 
Revision 1, dated February 12, 2009. Repeat the inspection 
thereafter at intervals not to exceed 1,500 flight cycles until the 
actions specified in paragraph (k) or (l) of this AD are 
accomplished.

Repair

    (k) If cracking is found during any inspection required by this 
AD: Before further flight, repair the affected stringer in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2484, dated June 26, 2003; or Boeing 
Service Bulletin 747-53A2484, Revision 1, dated February 12, 2009. 
After the effective date of this AD, use only Boeing Service 
Bulletin 747-53A2484, Revision 1, dated February 12, 2009. 
Accomplishment of the repair terminates the repetitive inspections 
required by this AD for that repaired stringer/frame location only.

Optional Terminating Action

    (l) Installing new frame clips and new doublers, and repairing 
as applicable, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2484, dated 
June 26, 2003; or Boeing Service Bulletin 747-53A2484, Revision 1, 
dated February 12, 2009; terminates the repetitive inspections 
required by this AD. After the effective date of this AD, use only 
Boeing Service Bulletin 747-53A2484, Revision 1, dated February 12, 
2009.

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. Send information to ATTN: 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; or e-mail 
information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) 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 principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (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.
    (4) AMOCs approved previously in accordance with AD 2005-15-08, 
amendment 39-14197, are approved as AMOCs for the corresponding 
provisions of this AD.

    Issued in Renton, Washington, on July 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-16575 Filed 7-13-09; 8:45 am]
BILLING CODE 4910-13-P