[Federal Register Volume 78, Number 70 (Thursday, April 11, 2013)]
[Proposed Rules]
[Pages 21576-21578]
From the Federal Register Online via the Government Publishing 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:
[email protected].
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: [email protected].
(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: [email protected].
(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]
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