[Federal Register Volume 75, Number 154 (Wednesday, August 11, 2010)]
[Proposed Rules]
[Pages 48623-48625]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-19832]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0796; Directorate Identifier 2010-NM-007-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 767-300 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
certain Model 767-300 series airplanes. This proposed AD would require
repetitive inspections for cracks in the fuselage skin and backup
structure at the lower very high frequency (VHF) antenna cutout at
station 1197 + 99 between stringers 39L and 39R, and corrective actions
if necessary. Certain repairs would terminate certain inspection
requirements. This proposed AD results from reports of cracking found
in the section 46 fuselage lower skin around the periphery of the VHF
antenna baseplate at station 1197 + 99. We are proposing this AD to
detect and correct fatigue cracks in the fuselage skin and internal
backup structure, which could result in rapid decompression of the
airplane.
DATES: We must receive comments on this proposed AD by September 27,
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 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 [email protected];
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 (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
[[Page 48624]]
Washington 98057-3356; telephone 425-917-6577; 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-2010-0796;
Directorate Identifier 2010-NM-007-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 been advised that two operators reported cracks found in
the section 46 fuselage lower skin around the periphery of the VHF
antenna baseplate at station 1197 + 99. One operator reported 5 cracks,
with a maximum length of 11 inches, found on an airplane that had
accumulated 38,804 total flight hours and 34,929 total flight cycles.
Another operator reported a maximum crack length of 9.5 inches found on
an airplane that had accumulated 60,467 total flight hours and 29,185
total flight cycles. Boeing investigation has revealed that the
fuselage skin and internal backup structural cracks are attributed to
fatigue. This fatigue is the result of bending loads in the skin caused
by vibration of the antenna in flight. No operator reported crack
findings for the backup structure. Fatigue cracks in the fuselage skin
and internal backup structure, if not corrected, could result in rapid
decompression of the airplane.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 767-53-
0207, dated December 17, 2009. The service bulletin describes
procedures for repetitive inspections for cracks in the fuselage skin
and backup structure at the lower VHF antenna cutout at station 1197 +
99, between stringers 39L and 39R. The inspections include an external
detailed inspection of the fuselage skin at the lower aft VHF antenna
cutout, and an internal detailed inspection of the backup structure.
Corrective actions include repairing fuselage skin cracks, which
would eliminate the need to repeat the external detailed inspection;
and repairing or replacing cracked backup structure parts.
In the service bulletin, the compliance time for the external
detailed inspection is before the accumulation of 25,000 total flight
cycles, or within 3,000 flight cycles after the date on the service
bulletin, whichever occurs later. The compliance time for the internal
detailed inspection is before the accumulation of 25,000 total flight
cycles, or within 3,000 flight cycles after the date on the service
bulletin, whichever occurs later; or the inspection may be deferred for
an additional 6,000 flight cycles if no fuselage skin cracks are found
during the external detailed inspection.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined that 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.
Costs of Compliance
We estimate that this proposed AD would affect 93 airplanes of U.S.
registry. The following table provides the estimated costs for U.S.
operators to comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Cost per registered Fleet cost
rate per hour product airplanes
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Inspections........................................................ 3 $85 $255 93 $23,715
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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), 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:
[[Page 48625]]
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:
The Boeing Company: Docket No. FAA-2010-0796; Directorate Identifier
2010-NM-007-AD.
Comments Due Date
(a) We must receive comments by September 27, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 767-300 series
airplanes, certificated in any category, as identified in Boeing
Special Attention Service Bulletin 767-53-0207, dated December 17,
2009.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of cracking found in the
section 46 fuselage lower skin around the periphery of the very high
frequency (VHF) antenna baseplate at station 1197 + 99. The Federal
Aviation Administration is issuing this AD to detect and correct
fatigue cracks in the fuselage skin and internal backup structure,
which could result in rapid decompression 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) Inspect for cracks in the fuselage skin and backup structure
at the lower VHF antenna cutout at station 1197 + 99, between
stringers 39L and 39R, by doing an external detailed inspection,
with the antenna removed, of the fuselage structure at the lower aft
VHF antenna cutout, and an internal detailed inspection of the
backup structure. Do the inspections in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 767-53-0207, dated December 17, 2009 (``the service
bulletin''). Do the inspections at the applicable time specified in
paragraph 1.E., ``Compliance,'' of the service bulletin, except,
where the service bulletin specifies a compliance after the date on
the service bulletin, this AD requires compliance within the
specified time after the effective date of this AD.
(1) If no crack is found, repeat the external detailed
inspection, without removing the antenna, at intervals not to exceed
3,000 flight cycles.
(2) If any crack is found in the fuselage, repair before further
flight, in accordance with the service bulletin. Accomplishment of
this repair terminates the repetitive external detailed inspections
of the fuselage skin required by this AD.
(3) If any crack is found in the backup structure, before
further flight, repair or replace the cracked part(s), in accordance
with the service bulletin.
Alternative Methods of Compliance (AMOCs)
(h)(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: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; telephone 425-917-6577; fax 425-
917-6590. Information may be e-mailed to [email protected].
(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 refer to 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.
Issued in Renton, Washington, on August 4, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-19832 Filed 8-10-10; 8:45 am]
BILLING CODE 4910-13-P