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[Federal Register Volume 76, Number 6 (Monday, January 10, 2011)]
[Rules and Regulations]
[Pages 1351-1354]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-51]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1280; Directorate Identifier 2010-NM-270-AD; 
Amendment 39-16572; AD 2011-01-15]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Model 757-200, -
200CB, and -300 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 the 
products listed above. This AD requires repetitive inspections for 
cracking of the fuselage skin of the crown skin panel along the chem-
milled step at stringers S-4 left and S-4 right, from stations (STA) 
297 through 439, and repair if necessary. This AD also includes 
terminating action for the repetitive inspections of the repaired areas 
only. This AD was prompted by reports of cracking in the fuselage skin 
of the crown skin panel. We are issuing this AD to detect and correct 
fatigue cracking of the fuselage skin of the crown skin panel, which 
could result in pressure venting and consequent rapid decompression of 
the airplane.

DATES: This AD is effective January 25, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 25, 
2011.
    We must receive comments on this AD by February 24, 2011.

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. 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.

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 (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6440; fax (425) 917-6590; e-mail: nancy.marsh@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received reports of cracking in the fuselage skin of the 
crown skin panel. On one airplane, the crack was 10.75 inches long, 
midway between stations (STA) 420 and 439, just above the lap joint at 
stringer 4L (left) of the chem-milled step. The airplane had 
accumulated 24,631 total flight cycles. On another airplane, there was 
an opening from a crack in the fuselage above and aft of the passenger 
entry doorway. One edge of the opening ran approximately 18 inches in 
the forward-to-aft direction; the other edge ran approximately 12 
inches along the chem-milled pocket edge above stringer 4L. 
Additionally, a 1.3-inch crack was found in the skin forward of the 
opening in the adjacent skin bay also in the chem-milled step above 
stringer 4L. The airplane had accumulated 22,450 total

[[Page 1352]]

flight cycles. The subject cracking is attributed to fatigue. Such 
cracking could initiate at multiple locations on the interior surface 
along the chem-milled step edges above the stringer 4L or 4R (right) 
lap splices of the skin. This condition, if not corrected, could result 
in pressure venting and consequent rapid decompression of the airplane.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 757-53-0097, 
dated November 22, 2010. The service information describes procedures 
for repetitive inspections for cracking of the fuselage skin of the 
crown skin panel along the chem-milled step at stringers S-4L and S-4R, 
from STA 297 through 439, as specified in the options below. If any 
crack is found, the service bulletin recommends contacting Boeing for 
damage removal and repair instructions.
     Option A Inspection: An external detailed inspection of 
the STA 297 through 439 crown skin panel at stringers S-4L and S-4R lap 
joints.
     Option B Inspection: An external sliding probe eddy 
current inspection of the STA 297 through 439 crown skin panel at 
stringers S-4L and S-4R lap joints.
     Option C Inspection: An external spot probe medium 
frequency eddy current inspection of the STA 297 through 439 crown skin 
panel at stringers S-4L and S-4R lap joints.
    The compliance time for all of the initial inspections is before 
the accumulation of 15,000 total flight cycles, or within 30 days after 
the original issue date of the service bulletin, whichever occurs 
later. The repetitive interval is specified below.
     Option A: At intervals not to exceed 30 flight cycles.
     Option B: At intervals not to exceed 300 flight cycles.
     Option C: At intervals not to exceed 200 flight cycles.
    The initial external detailed inspection specified in Option A, if 
done, is repeated until either the Option B or Option C inspection is 
accomplished within 90 days after the original date of the service 
bulletin, and thereafter, either the Option B or Option C inspection is 
repeated. Accomplishing the Option B or Option C inspection would 
eliminate the need for the Option A inspection.
    A detailed external inspection may be applied no more than once for 
each repeat interval of 300 flight cycles to extend the Option B repeat 
inspection up to 330 flight cycles, and for each repeat interval of 200 
flight cycles to extend the Option C inspection up to 230 flight 
cycles--not to exceed 30 flight cycles after accomplishing the 
inspection.
    Boeing Special Attention Service Bulletin 757-53-0097, dated 
November 22, 2010, also includes certain exceptions to the inspection 
of the edge of the chem-milled pocket under an existing external repair 
doubler.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Difference Between the AD and the Service Information.''

Difference Between the AD and the Service Information

    Boeing Special Attention Service Bulletin 757-53-0097, dated 
November 22, 2010, 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:
     In accordance with 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) whom we have 
authorized to make those findings.

Interim Action

    We consider this AD interim action. An investigation is ongoing and 
no terminating action has been developed yet.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
fatigue cracking of the fuselage skin of the crown skin panel could 
result in pressure venting and consequent rapid decompression of the 
airplane. Therefore, we find that notice and opportunity for prior 
public comment are impracticable and that good cause exists for making 
this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. 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- 2010-1280; Directorate 
Identifier 2010-NM-270-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.

Costs of Compliance

    We estimate that this AD affects 683 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
           Action                  Labor cost                 Parts cost             Cost per product                 Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection.................  1 work-hour x $85 per   None.......................  $85 per inspection      $58,055 per inspection cycle.
                              hour = $85 per                                       cycle.
                              inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 1353]]

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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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 airworthiness 
directive (AD):

2011-01-15 The Boeing Company: Amendment 39-16572; Docket No. FAA-
2010-1280; Directorate Identifier 2010-NM-270-AD.

Effective Date

    (a) This AD is effective January 25, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 757-200, -200CB, 
and -300 series airplanes, certificated in any category, as 
identified in Boeing Special Attention Service Bulletin 757-53-0097, 
dated November 22, 2010.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 53: Fuselage.

Unsafe Condition

    (e) This AD was prompted by reports of cracking in the fuselage 
skin of the crown skin panel. We are issuing this AD to detect and 
correct fatigue cracking of the fuselage skin, which could result in 
pressure venting and consequent rapid decompression of the airplane.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Repetitive Inspections/Repair

    (g) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-
0097, dated November 22, 2010, except as required by paragraph (i) 
of this AD: Do an external detailed, sliding probe eddy current, or 
spot-probe-medium-frequency eddy current inspection for cracking of 
the fuselage skin of the crown skin panel along the chem-milled step 
at stringers S-4L (left) and S-4R (right), stations (STA) 297 
through 439, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 757-53-0097, dated 
November 22, 2010. Repeat the applicable inspection thereafter at 
the interval specified in paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 757-53-0097, dated November 22, 
2010.

Repair

    (h) If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (j) of this AD. Doing the repair ends the repetitive 
inspections for the repaired area only.

Exception to Service Bulletin Specification

    (i) Where Boeing Special Attention Service Bulletin 757-53-0097, 
dated November 22, 2010, 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.

Alternative Methods of Compliance (AMOCs)

    (j)(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. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.
    (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.

Related Information

    (k) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6440; fax (425) 917-6590; e-mail: 
nancy.marsh@faa.gov.

Material Incorporated by Reference

    (l) You must use Boeing Special Attention Service Bulletin 757-
53-0097, dated November 22, 2010, to do the actions required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of the 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 an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

[[Page 1354]]

    Issued in Renton, Washington, on December 28, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-51 Filed 1-7-11; 8:45 am]
BILLING CODE 4910-13-P
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