[Federal Register Volume 75, Number 37 (Thursday, February 25, 2010)]
[Proposed Rules]
[Pages 8554-8557]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-3819]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0132; Directorate Identifier 2009-NM-096-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-100, -
200B, and -200F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Model 747-100, 747-200B, and -
200F series airplanes. The existing AD currently requires inspections
to detect cracking in the upper row of fasteners holes of the skin lap
joints in the fuselage lower lobe, and repair, if necessary. This
proposed AD would reduce the maximum interval of the post-modification
inspections. This proposed AD results from reports of fatigue cracking
on modified airplanes. We are proposing this AD to detect and correct
fatigue cracking in the longitudinal lap joints of the fuselage lower
lobe, which could lead to the rapid decompression of the airplane and
the inability of the structure to carry fail-safe loads.
DATES: We must receive comments on this proposed AD by April 12, 2010.
ADDRESSES: You may send comments by any of the following methods:
[[Page 8555]]
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 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-2010-0132;
Directorate Identifier 2009-NM-096-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
On August 4, 1994, we issued AD 94-17-01, Amendment 39-8996 (59 FR
41653, August 15, 1994), for certain Model 747 series airplanes. That
AD requires inspections to detect cracking in the upper row of fastener
holes of the skin lap joints in the fuselage lower lobe, and repair if
necessary. That AD resulted from reports of incidents involving fatigue
cracking and corrosion of transport category airplanes that are
approaching or have exceeded their design life goal. We issued that AD
to prevent separation of fuselage skin and rapid loss of pressure in
the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 94-17-01, Boeing has performed a fleet-wide
evaluation of the skin panel lap joints for widespread fatigue damage
(WFD) and determined that the post-modification inspection interval of
AD 94-17-01 needs to be reduced. In addition, lap joints where the
upper (overlapping) skin thickness at the upper row of fasteners is
0.071 inch or less need to be further modified to preclude WFD. WFD of
the lap joints can link up and result in large skin cracks, and
possible rapid in-flight decompression of the airplane.
Relevant Service Information
AD 94-17-01 referred to Boeing Service Bulletin 747-53A2267,
Revision 3, dated March 26, 1992, as the appropriate source of service
information. Boeing has since issued Alert Service Bulletin 747-
53A2267, Revision 4, dated March 26, 2009. This service bulletin
reduces the repetitive interval for the post-modification inspections
and references a structural modification for lap joints where the upper
(overlapping) skin thickness at the upper row of fasteners is 0.071
inch or less.
Related Rulemaking
We are considering issuing related rulemaking to address the
identified unsafe condition. We are in the process of issuing an AD
that will refer to Revision 1 of Boeing Alert Service Bulletin 747-
53A2463, and is related to this issue. That AD will require further
modification of all the affected lap joints with an upper skin
thickness of 0.071 inch or less.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 94-17-01. This AD would retain the requirements of
that AD using the revised service information, and reduce the maximum
interval of the post-modification inspections from 3,000 flight cycles
to 1,000 flight cycles.
Differences Between the Proposed AD and Service Bulletin
Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March
26, 2009, 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 the Boeing Commercial
Airplanes Organization Designation Authorization that we have
authorized to make those findings.
Changes to Existing AD
This proposed AD would retain the requirements of AD 94-17-01.
Since AD 94-17-01 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 94-17-01 proposed AD
------------------------------------------------------------------------
Paragraph (a) Paragraph (g).
Paragraph (b) Paragraph (h).
Paragraph (c) Paragraph (i).
------------------------------------------------------------------------
This proposed AD identifies the legal name of the manufacturer as
published in the most recent type certificate data sheet for the
affected airplane models.
Costs of Compliance
There are about 23 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
[[Page 8556]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S. -
Action Work hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 94-17-01) 244 $85 $0 $20,740 per inspection 7 $145,180 per inspection cycle.
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 have 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 that the 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
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 removing Amendment 39-8996 (59 FR
41653, August 15, 1994) and adding the following new AD:
The Boeing Company: Docket No. FAA-2010-0132; Directorate Identifier
2009-NM-096-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 12,
2010.
Affected ADs
(b) This AD supersedes AD 94-17-01, Amendment 39-8996.
Applicability
(c) This AD applies to The Boeing Company Model 747-100, 747-
200B, and 747-200F series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin 747-53A2267, Revision
4, dated March 26, 2009.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of fatigue cracking. The
Federal Aviation Administration is issuing this AD to detect and
correct fatigue cracking in the fuselage lower lobe longitudinal lap
joints, which could lead to the rapid decompression of the airplane
and the inability of the structure to carry fail-safe loads.
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.
Restatement of Requirements of AD 94-17-01, with Revised
Compliance Times for Post-Modification Inspection and Revised
Service Information:
Initial External High Frequency Eddy Current Inspection
(g) Perform an external high frequency eddy current inspection
to detect cracks in the upper row of fasteners in the modified lap
joints in accordance with Boeing Service Bulletin 747-53A2267,
Revision 3, dated March 26, 1992; or Revision 4, dated March 26,
2009; at the time specified in paragraph (g)(1) or (g)(2) or (g)(3)
of this AD, as applicable. As of the effective date of this AD, only
Revision 4 may be used.
(1) For airplanes on which the full modification required by AD
90-06-06, Amendment 39-6490, has been accomplished in accordance
with Revision 2 of Boeing Service Bulletin 747-53A2267, dated March
29, 1990; or Revision 3, dated March 26, 1992; or Revision 4, dated
March 26, 2009: Prior to the accumulation of 10,000 flight cycles
after accomplishment of the full modification.
(2) For airplanes on which the full modification required by AD
90-06-06 has been accomplished in accordance with Boeing Service
Bulletin 747-53A2267, dated March 28, 1986; or Revision 1, dated
September 25, 1986: Prior to the accumulation of 7,000 flight cycles
after accomplishment of the full modification.
(3) For airplanes on which the optional modification has been
accomplished in accordance with Boeing Service Bulletin 747-53A2267,
Revision 2, dated March 29, 1990; or Revision 3, dated March 26,
1992; or Revision 4, dated March 26, 2009: Prior to the accumulation
of 7,000 flight cycles after accomplishment of the optional
modification.
Repetitive External High Frequency Eddy Current Inspections
(h) If no cracking is detected during the inspection required by
paragraph (g) of this AD, repeat the inspection required by
paragraph (g) of this AD at the earlier of the times specified in
paragraphs (h)(1) and (h)(2) of this AD, and thereafter at intervals
not to exceed 1,000 flight cycles.
(1) Within 3,000 flight cycles after the last inspection
required by paragraph (g) of this AD.
(2) Within 1,000 flight cycles after the last inspection
required by paragraph (g) of this AD or 500 flight cycles after the
effective date of this AD, whichever occurs later.
Repair
(i) If any cracking is detected during any inspection required
by paragraph (g) of this
[[Page 8557]]
AD, prior to further flight, repair in accordance with Section 53-
30-03 of the Boeing 747 Structural Repair Manual (SRM); or Boeing
Alert Service Bulletin 747-53A2267, Revision 4, dated March 26,
2009; except as required by paragraph (j) of this AD; and repeat the
inspection required by paragraph (g) of this AD at the times
specified in paragraph (i)(1) of this AD. After the effective date
of this AD, use only Boeing Alert Service Bulletin 747-53A2267,
Revision 4, dated March 26, 2009.
(1) As of the effective date of this AD: If the repair specified
in the Boeing 747 SRM does not include removing the lap joint and
the upper row of countersunk fasteners, repeat the inspection
required by paragraph (g) of this AD at the earlier of the times
specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, and
thereafter at intervals not to exceed 1,000 flight cycles.
(i) Within 3,000 flight cycles after the last inspection
required by paragraph (g) of this AD.
(ii) Within 1,000 flight cycles after the last inspection
required by paragraph (g) of this AD, or within 500 flight cycles
after the effective date of this AD, whichever occurs later.
(2) If the repair specified in the 747 SRM includes removing the
lap joint and the upper row of countersunk fasteners, such repair
constitutes terminating action for the inspection requirements of
this AD.
Exception to the Service Bulletin
(j) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 747-53A2267, Revision 4,
dated March 26, 2009, specifies contacting Boeing for appropriate
action: Before further flight, repair the cracking using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD. For a repair method to be approved by the Manager,
Seattle ACO, as required by this paragraph, the Manager's approval
letter must specifically refer to this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office, 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 [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 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 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.
(4) AMOCs approved previously in accordance with AD 94-17-01 are
approved as AMOCs for the corresponding provisions of this AD.
Issued in Renton, Washington, on February 17, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-3819 Filed 2-24-10; 8:45 am]
BILLING CODE 4910-13-P