Document ID: FAA-2009-0794-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP Series Airplanes
Posted Date: 2009-09-28T04:00Z

[Federal Register: September 28, 2009 (Volume 74, Number 186)]
[Proposed Rules]               
[Page 49351-49354]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28se09-19]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0794; Directorate Identifier 2009-NM-035-AD]
RIN 2120-AA64

 
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Boeing Model 747 airplanes. This proposed AD would require a general 
visual inspection to identify any existing repairs of the upper main 
sill outer chord of the left and right side main entry door number 1, 
as applicable; repetitive detailed inspections for cracks in the upper 
main sill of the door(s); and related investigative and corrective 
actions, if necessary. This proposed AD would also require repetitive 
inspections for airplanes on which a certain repair is done, and 
corrective actions if necessary. This proposed AD results from reports 
of cracks in the main entry door number 1 upper main sill outer chord, 
along the bend radius of the chord on several airplanes. We are 
proposing this AD to detect and correct such cracks, which could result 
in loss of structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by November 12, 
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.

[[Page 49352]]

     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:[sol][sol]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-2009-0794; 
Directorate Identifier 2009-NM-035-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

    We have received reports in the main entry door number 1 upper main 
sill outer chord, along the bend radius of the chord on several 
airplanes. The cracks have been attributed to fatigue. This condition, 
if not detected and corrected, could result in loss of structural 
integrity of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009. The service bulletin describes procedures for a 
general visual inspection to identify any existing structural repair 
manual (SRM) repairs of the upper main sill outer chord of the left and 
right side main entry door number 1, as applicable, repetitive detailed 
inspections to detect cracks in the upper main sill of the door(s), and 
related investigative and corrective actions, if necessary.
    The related investigative action is to remove any existing SRM 
outer chord repair found and do a detailed inspection for cracks of the 
upper main sill and corrective actions, if necessary.
    The corrective actions include:
     For airplanes on which any crack is found in the upper 
main sill outer chord, install an outer chord repair in accordance with 
Boeing drawing 691U0145;
     For airplanes on which any existing SRM outer chord repair 
is removed, install a new repair in accordance with Boeing drawing 
691U0145;
     For airplanes on which any crack is found in the frame 
attachment angles or clips of the upper main sill, replace the cracked 
angle or clip with a new part; and
     For airplanes on which any crack is found in the upper 
main sill web, contact Boeing for repair instructions.
    The service bulletin also describes procedures for repetitive 
after-repair inspections of any upper main sill(s) that has been 
repaired in accordance with Boeing drawing 691U0145. For airplanes on 
which any crack is found during the after-repair inspections, the 
service bulletin specifies contacting Boeing for repair instructions.
    The compliance time for the initial general visual and detailed 
inspections is before 9,000 total flight cycles or within 12,000 flight 
cycles after installation of the Zone 3 modification in accordance with 
Boeing Service Bulletin 747-53-2272, depending on the configuration of 
the airplane; or within 1,500 flight cycles after the date on the 
service bulletin; whichever occurs later. The repetitive interval for 
the detailed inspection is 6,000 flight cycles. The compliance time for 
the after-repair inspection is within 15,000 flight cycles after the 
installation of the repair in accordance with Boeing drawing 691U0145, 
or within 1,500 flight cycles after the date on the service bulletin, 
whichever occurs later. The repetitive interval for the after-repair 
inspection is 3,000 flight cycles. The compliance time for all related 
investigative and corrective actions is before further flight.

FAA's Determination and Requirements of this Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously, except as discussed under 
``Differences Between the Proposed AD and the Service Bulletin.''

Differences between the Proposed AD and the Service Bulletin

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed 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 an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.
    Where the service bulletin specifies a compliance time after the 
date on the service bulletin, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

Costs of Compliance

    We estimate that this proposed AD would affect 165 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

[[Page 49353]]

                                                                 Table--Estimated Costs
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                                                     Average labor                                             Number of U.S.-
              Action                  Work hours     rate per hour       Parts         Cost per product     registered airplanes         Fleet cost
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Inspection (groups 1, 3)..........               6             $80              $0  $480, per inspection   Up to 165.............  Up to $79,200, per
                                                                                     cycle.                                         inspection cycle.
Inspection (groups 2, 4)..........               3              80               0  $240, per inspection   Up to 165.............  Up to $39,600, per
                                                                                     cycle.                                         inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 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 this 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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 adding the following new AD:

Boeing: Docket No. FAA-2009-0794; Directorate Identifier 2009-NM-
035-AD.

Comments Due Date

    (a) We must receive comments by November 12, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP series airplanes, certificated in any 
category.

Subject

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

Unsafe Condition

    (e) This AD results from reports of cracks in the main entry 
door number 1 upper main sill outer chord, along the bend radius of 
the chord on several airplanes. The Federal Aviation Administration 
is issuing this AD to detect and correct such cracks, which could 
result in 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) At the applicable times specified in Table 1 of paragraph 
1.E. ``Compliance'' of Boeing Alert Service Bulletin 747-53A2785, 
dated February 12, 2009, except as required by paragraphs (j), (k), 
and (l) of this AD: Do a general visual inspection to identify any 
existing structural repair manual (SRM) repairs of the upper main 
sill outer chord of the left and right side main entry door number 
1, as applicable; a detailed inspection for cracks in the upper main 
sill of the door(s); and do all related investigative and corrective 
actions, as applicable; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009. Do all applicable related investigative and 
corrective actions before further flight.
    (h) For airplanes identified in paragraphs (h)(1) and (h)(2) of 
this AD: Repeat the detailed inspection described in paragraph (g) 
of this AD thereafter at the interval specified in Table 1 of 
paragraph 1.E. ``Compliance'' of Boeing Alert Service Bulletin 747-
53A2785, dated February 12, 2009, until the outer chord repair 
specified in drawing 691U0145 is done on the upper main sill, in 
accordance with the Accomplishment Instructions of the Boeing Alert 
Service Bulletin 747-53A2785, dated February 12, 2009.
    (1) Airplanes on which no cracking is found and no existing SRM 
outer chord repair is found during any inspection required by 
paragraph (g) of this AD.
    (2) Airplanes on which sill web or frame attachment angles (or 
clips) are repaired or replaced in accordance with Boeing Alert 
Service Bulletin 747-53A2785, dated February 12, 2009, and the 
drawing 691U0145 outer chord repair is not installed in accordance 
with Boeing Alert Service Bulletin 747-53A2785, dated February 12, 
2009.
    (i) For airplanes on which the outer chord repair specified in 
drawing 691U0145 has been installed in accordance with Boeing Alert 
Service Bulletin 747-53A2785, dated February 12, 2009: At the 
applicable times specified in Table 2 of paragraph 1.E. 
``Compliance'' of Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009, except as required by paragraph (l) of this AD, 
do the after-repair inspections and all applicable corrective 
actions in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2785, dated February 12, 2009, except 
as provided by paragraph (k) of this AD. Repeat the inspections 
thereafter at intervals not to exceed 3,000 flight cycles.

Credit for Inspections Required by AD 2005-20-30 or AD 2006-05-02

    (j) Accomplishing the inspections required by AD 2005-20-30 or 
AD 2006-05-02, as applicable, is an acceptable method of compliance 
for the inspections required by paragraph (g) of this AD. For any 
airplane that has accumulated 22,000 total flight

[[Page 49354]]

cycles or more, AD 2005-20-30 requires accomplishing the inspections 
in accordance with Boeing Service Bulletin 747-53A2349, Revision 2, 
dated April 3, 2003; and AD 2006-05-02 requires accomplishing the 
inspections in accordance with Boeing Alert Service Bulletin 747-
53A2500, dated December 21, 2004.

Exceptions to the Service Bulletin

    (k) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2785, dated February 
12, 2009, specifies to contact Boeing for appropriate action: Before 
further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.
    (l) Where Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009, specifies a compliance time ``after the date on 
this service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date 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. 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, and the approval must specifically refer to this 
AD.

    Issued in Renton, Washington, on September 18, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-23294 Filed 9-25-09; 8:45 am]

BILLING CODE 4910-13-P