
[Federal Register: April 29, 2010 (Volume 75, Number 82)]
[Rules and Regulations]               
[Page 22514-22516]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29ap10-6]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0381; Directorate Identifier 2009-NM-146-AD; 
Amendment 39-16268; AD 2010-09-03]
RIN 2120-AA64

 
Airworthiness Directives; The Boeing Company Model 747-200B 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Model 747-200B series airplanes. This AD requires repetitive 
inspections for cracking of the fuselage skin lap joints at stringer 6 
on the left and right sides from station (STA) 340 to STA 400, a one-
time general visual inspection to determine if certain fasteners are 
installed and to determine if service repair manual (SRM) repairs or 
repair doublers are installed, and corrective actions if necessary. 
Doing an optional modification of the stringer 6 lap joints terminates 
the repetitive inspections for the modified area. This AD results from 
reviews done by Boeing, which show that airplanes that were modified by 
Boeing to the stretched upper deck (SUD) configuration require 
inspection for cracking of the stringer 6 lap joint upper-fastener row 
earlier than previously expected. We are issuing this AD to detect and 
correct cracking of the stringer 6 lap joints where certain external 
doublers were not installed, which could result in rapid decompression 
and loss of structural integrity of the airplane.

DATES: This AD is effective May 14, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 14, 2010.
    We must receive comments on this AD by June 28, 2010.

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 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.

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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone 800-647-

[[Page 22515]]

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: 

Discussion

    Review by Boeing has determined that airplanes that were modified 
by Boeing to the stretched upper deck (SUD) configuration require 
inspecting the stringer 6 lap joint upper fastener row for cracking at 
an earlier time than expected. Previously, no inspections of this area 
were recommended prior to accomplishment of Boeing Service Bulletin 
747-53-2272, Zone 1 modification, which involves installing external 
doublers. If the external doublers have not been installed on the 
stringer 6 lap joints, cracks could develop in the lap joints. Skin 
cracks could join together and result in rapid decompression and loss 
of structural integrity of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2809, dated June 
18, 2009. This service bulletin specifies that, for airplanes with 
external doublers installed in accordance with Boeing Service Bulletin 
747-53-2272, no further work is necessary.
    For the other affected airplanes, Boeing Alert Service Bulletin 
747-53A2809, dated June 18, 2009, describes procedures for repetitive 
external detailed and high frequency eddy current (HFEC) inspections to 
detect cracking of the left and right side stringer 6 lap joints, doing 
a one-time general visual inspection to determine whether certain 
fasteners exist in the upper-fastener row of the lap joints and to 
determine whether any service repair manual (SRM) repairs or repair 
doublers are installed, and corrective actions if necessary. Corrective 
actions include repairing any cracks that are found, and contacting 
Boeing for repair instructions if certain fasteners, or if any SRM 
repairs or repair doublers other than those installed per Boeing 
Service Bulletin 747-53-2272,
    Zone 1 modification, are found in the inspection area.
    Boeing Alert Service Bulletin 747-53A2809, dated June 18, 2009, 
also specifies that the optional accomplishment of a modification would 
eliminate the need to do the repetitive inspections, repair cracks, or 
contact Boeing for instructions if certain fasteners are found. This 
modification involves removing the upper row of fasteners at the 
stringer 6 lap joints from STA 340 to STA 400 doing open-hole HFEC 
inspections to detect skin cracks; and doing corrective actions if 
necessary (e.g., trimming out any cracks found during any inspection), 
and installing external doublers as specified in the Zone 1 
modification of Boeing Service Bulletin 747-53-2272.
    The compliance time for the initial inspections is 10,000 flight 
cycles after the airplane was modified to the SUD configuration, or 
within 50 flight cycles after the date on Boeing Alert Service Bulletin 
747-53A2809, whichever occurs later. The repetitive interval is 3,000 
flight cycles. The compliance time for the corrective actions is before 
further flight.

FAA's Determination and Requirements of This AD

    No Model 747-200B series airplanes affected by this AD are on the 
U.S. Register. We are issuing this AD because the unsafe condition 
described previously is likely to exist or develop on other products of 
the same type design that could be registered in the United States in 
the future. This AD requires repetitive inspections of the left and 
right side stringer 6 lap joints from STA 340 to STA 400.
    Since no U.S. Model 747-200B series airplanes are affected by this 
AD, notice and opportunity for public comment before issuing this AD 
are unnecessary.

Differences Between the AD and the Service Information

    Boeing Alert Service Bulletin 747-53A2809, dated June 18, 2009, 
specifies to contact the manufacturer for instructions on how to repair 
certain conditions, but this 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 the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) that has been 
authorized by the Manager, Seattle ACO, to make those findings.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2010-0381; Directorate Identifier 2009-NM-146-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this 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 AD.

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

    This AD will not have federalism implications under Executive Order 
13132. This 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD docket.

[[Page 22516]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2010-09-03 The Boeing Company: Amendment 39-16268. Docket No. FAA-
2010-0381; Directorate Identifier 2009-NM-146-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective May 14, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 747-200B series 
airplanes, certificated in any category, identified as Group 1, 
Configuration 2, in Boeing Alert Service Bulletin 747-53A2809, dated 
June 18, 2009.

Subject

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

Unsafe Condition

    (e) This AD results from reviews done by Boeing, which show that 
airplanes modified to the stretched upper deck (SUD) configuration 
by Boeing require inspection for cracking of the upper-fastener row 
of the left and right side stringer 6 lap joints earlier than 
expected. The Federal Aviation Administration is issuing this AD to 
detect and correct cracking of the stringer 6 lap joints where 
certain external doublers were not installed, which could result in 
rapid decompression and loss of structural integrity 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.

Inspections

    (g) Except as required by paragraphs (h) and (i) of this AD: At 
the applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2809, dated June 18, 2009, do 
the inspections specified in paragraphs (g)(1) and (g)(2) of this 
AD, and applicable corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2809, dated June 18, 2009. Do all applicable corrective actions 
before further flight. Repeat the inspections specified in paragraph 
(g)(1) of this AD thereafter at intervals not to exceed 3,000 flight 
cycles, except as provided by paragraph (j) of this AD.
    (1) Inspect the left and right side stringer 6 lap joints from 
station (STA) 340 to STA 400. The inspections include external 
detailed and high frequency eddy current (HFEC) inspections for 
cracks in the skin in areas that have not been modified or repaired 
as specified in paragraph 3.B., Part 2 or Part 3, respectively, of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2809, dated June 18, 2009.
    (2) Do a one-time general visual inspection of the lap joints to 
determine if certain fasteners are installed and to determine if 
structural repair manual (SRM) repairs or repair doublers are 
installed.

    Note 1: For airplanes on which external doublers have been 
installed on both side of the airplanes in accordance with Boeing 
Service Bulletin 747-53-2272, Zone 1 modification, no further work 
is necessary.

Exceptions to Service Bulletin

    (h) Where Boeing Alert Service Bulletin 747-53A2809, dated June 
18, 2009, specifies a compliance time after the date on that service 
bulletin, this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (i) For any condition in which Boeing Alert Service Bulletin 
747-53A2809, dated June 18, 2009, specifies to contact Boeing for 
appropriate action: those actions must be approved using a method 
approved in accordance with the procedures specified in paragraph 
(k) of this AD.

Optional Terminating Action

    (j) Accomplishing the modification, including the open-hole HFEC 
inspections to detect skin cracks, and applicable corrective 
actions, specified in paragraph 3.B., Part 2, of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2809, dated 
June 18, 2009, terminates the repetitive inspections and repair 
requirements specified in paragraph (g) of this AD for the side of 
the airplane on which the modification is done.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle Aircraft Certification Office (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 ACO, 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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that 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.

Material Incorporated by Reference

    (l) You must use Boeing Alert Service Bulletin 747-53A2809, 
dated June 18, 2009, to do the actions required by this AD, unless 
the AD specifies otherwise. If you accomplish the optional 
terminating actions specified by this AD, you must use Boeing Alert 
Service Bulletin 747-53A2809, dated June 18, 2009, as applicable, to 
perform those actions, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this 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.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on April 9, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service..
[FR Doc. 2010-9091 Filed 4-28-10; 8:45 am]
BILLING CODE 4910-13-P

