
[Federal Register Volume 78, Number 70 (Thursday, April 11, 2013)]
[Proposed Rules]
[Pages 21576-21578]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-08450]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0300; Directorate Identifier 2011-NM-163-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company 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 
certain The Boeing Company Model 757-200, 757-200CB, and 757-200PF 
airplanes. This proposed AD was prompted by a report that a forward-
most cam latch of the forward center cam latch pair on a main cargo 
door (MCD) broke during flight. This proposed AD would require 
performing repetitive inspections of the MCD cam latches; replacing cam 
latches, certain bolts, and door hinge fittings; performing related 
investigative and corrective actions, if necessary; and MCD rigging. We 
are proposing this AD to detect and correct cracked or damaged cam 
latches, latch pins, and latch pin cross bolts, which could reduce the 
structural integrity of the MCD, and result in potential rapid 
decompression of the airplane and potential loss of the cargo door from 
the airplane.

DATES: We must receive comments on this proposed AD by May 28, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above 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; 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 proposed 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: Kimberly DeVoe, Aerospace Engineer, 
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: (425) 917-6495; fax: (425) 917-6590; email: 
kimberly.devoe@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2013-0300; 
Directorate Identifier 2011-NM-163-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 received a report that the forward-most cam latch on the forward 
center cam latch pair on a main cargo door (MCD) broke during flight on 
a Model 757 airplane. Cracked or damaged cam latches, latch pins, and 
latch pin cross bolts, if not corrected, could reduce the structural 
integrity of the MCD, and result in potential rapid decompression of 
the airplane and potential loss of the

[[Page 21577]]

cargo door from the airplane. Two of the eight cam latches or latch 
pins being broken in close proximity will cause loss of the cargo door 
during flight.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 757-52A0091, dated March 
9, 2010. For information on the procedures and compliance times, see 
this service information at http://www.regulations.gov by searching for 
Docket No. FAA-2013-0300.

FAA's Determination

    We are proposing 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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information identified previously under ``Relevant 
Service Information,'' except as discussed under ``Differences Between 
the Proposed AD and the Service Information.''
    The phrase ``related investigative actions'' might be used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, and (2) are actions that 
further investigate the nature of any condition found. Related 
investigative actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Differences Between the Proposed AD and the Service Information

    The Accomplishment Instructions of Boeing Alert Service Bulletin 
757-52A0091, dated March 9, 2010, specify to contact the manufacturer 
for disposition of certain repair conditions, this proposed AD would 
require operators to repair those conditions using a method approved by 
the FAA.

Costs of Compliance

    We estimate that this proposed AD affects 9 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
             Action                      Labor cost              Parts cost           product        operators
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Inspections/Modification........  55 work-hours x $85 per   None................          $4,675         $42,075
                                   hour = $4,675.
Replace cross bolts.............  3 work-hours x $85 per    $0..................             255           2,295
                                   hour = $255.
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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 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),
    (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.

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

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):

The Boeing Company: Docket No. FAA-2013-0300; Directorate Identifier 
2011-NM-163-AD.

(a) Comments Due Date

    We must receive comments by May 28, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, 757-200CB, 
and 757-200PF airplanes; certified in any category; as identified in 
Boeing Alert Service Bulletin 757-52A0091, dated March 9, 2010.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 52, Doors.

(e) Unsafe Condition

    This AD was prompted by a report that a forward most cam latch 
on the forward center cam latch pair on a main cargo door (MCD) 
broke during flight. We are issuing to detect and correct cracked or 
damaged cam latches, latch pins, and latch pin cross bolts, which 
could reduce the structural integrity of the MCD, and result in 
potential rapid decompression of the airplane and potential loss of 
the cargo door from the airplane.

(f) Compliance

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

(g) MCD Inspections, Bolt Torque, Latch Pin Measurement, Bolt 
Replacement, and Rigging

    At the applicable times specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 757-52A0091, dated 
March 9, 2010, except as specified in

[[Page 21578]]

paragraph (l)(2) of this AD: Do a detailed inspection of the cam 
latches and latch pins to detect damage, distress, and incorrect 
rigging; torque the cross bolts; measure the extension of the latch 
pins; replace all alloy steel bolts used as latch pin cross bolts 
with corrosion resistant steel (CRES) bolts; rig the MCD, as 
applicable; and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-52A0091, dated 
March 9, 2010, except as required by paragraph (l)(2) of this AD. Do 
all applicable related investigative and corrective actions at the 
applicable time specified in paragraph 1.E., ``Compliance'' of 
Boeing Alert Service Bulletin 757-52A0091, dated March 9, 2010.

(h) Repetitive Inspections

    Repeat the applicable inspections specified in paragraph (g) of 
this AD, as specified in paragraphs (h)(1), (h)(2), and (h)(3) of 
this AD, at the applicable times specified in table 1 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 757-52A0091, 
dated March 9, 2010. The inspection conditions are defined in Boeing 
Alert Service Bulletin 757-52A0091, dated March 9, 2010.
    (1) For airplanes found with Inspection Condition 5: Repeat the 
general visual inspection for broken, cracked, missing, or migrated 
parts of the cam latches and latch pins.
    (2) For airplanes found with Inspection Condition 2, 4.2, or 5: 
Repeat the detailed inspection for damage, distress, and incorrect 
rigging of the cam latches and latch pins.
    (3) For airplanes found with Inspection Condition 5: Repeat the 
high frequency eddy current or magnetic particle inspection to 
detect signs of cracking of cam latches 1 and 2.

(i) MCD Post-Rigging Initial Inspections and Related Investigative and 
Corrective Actions

    At the applicable times specified in table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 757-52A0091, dated 
March 9, 2010: Do a general visual inspection of the cam latches and 
latch pins for discrepancies; a detailed inspection of the cam 
latches and latch pins for discrepancies; and an HFEC or magnetic 
particle inspection of cam latch 1 and cam latch 2 for cracking; and 
do all applicable related investigative and corrective actions, 
except as required by paragraph (l)(2) of this AD; in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 757-52A0091, dated March 9, 2010. Do all applicable related 
investigative and corrective actions at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-52A0091, dated March 9, 2010.

(j) MCD Post-Rigging Repetitive Inspections

    (1) For all airplanes: Repeat the inspections specified in 
paragraph (i) of this AD, at the applicable times specified in table 
2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-52A0091, dated March 9, 2010.
    (2) For airplanes found with Inspection Condition 2 as defined 
in Boeing Alert Service Bulletin 757-52A0091, dated March 9, 2010: 
Repeat the detailed inspection for damage, distress, and incorrect 
rigging of the cam latches and latch pins specified in paragraph (i) 
of this AD on remaining cam latches and cam pins at the applicable 
times specified in table 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 757-52A0091, dated March 9, 2010.

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an 
alloy steel bolt as a cross bolt through any latch pin fitting 
assembly in the lower sill of the MCD on any airplane.

(l) Exceptions to Service Bulletin Specifications

    The following exceptions apply in this AD.
    (1) Where Boeing Alert Service Bulletin 757-52A0091, dated March 
9, 2010, specifies a compliance time after the date of that service 
bulletin, this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (2) Where Boeing Alert Service Bulletin 757-52A0091, dated March 
9, 2010, specifies to contact Boeing for appropriate action: Before 
further flight, repair the discrepancy in accordance with a method 
approved by the Manager, Seattle, Aircraft Certification Office 
(ACO), FAA. 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.

(m) Alternative Methods of Compliance (AMOCs)

    (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 emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
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.

(n) Related Information

    (1) For more information about this AD, contact Kimberly DeVoe, 
Aerospace Engineer, Cabin Safety and Environmental Systems Branch, 
ANM-150S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6495 ; fax: 
(425) 917-6590; email: kimberly.devoe@faa.gov.
    (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; 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.

    Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08450 Filed 4-10-13; 8:45 am]
BILLING CODE 4910-13-P


