[Federal Register Volume 76, Number 84 (Monday, May 2, 2011)]
[Rules and Regulations]
[Pages 24349-24351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-9919]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1111; Directorate Identifier 2010-NM-129-AD;
Amendment 39-16676; AD 2011-09-14]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-200B, -
300, -400, -400D, and -400F Series Airplanes Powered by Pratt and
Whitney 4000 or General Electric CF6-80C2 Series Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD requires an inspection to determine the
part number of the mid-pivot access door and to determine if the
correct door is installed, and the installation of a marker on the mid-
pivot access door, and if necessary, repetitive ultrasonic inspections
for cracking of the mid-pivot bolt assembly and eventual replacement of
the mid-pivot bolt assembly. This AD was prompted by a report that the
left and right access doors of the spring beam mid-pivot bolt assembly
for the No. 1 strut were inadvertently installed in the incorrect
position during strut modification. We are issuing this AD to detect
and correct incorrectly installed mid-pivot bolt assemblies on the
spring beam on the outboard struts. Incorrectly installed bolt
assemblies could lead to fatigue cracking and consequent fracturing of
the mid-pivot bolt assembly, which could lead to loss of the spring
beam load path and the possible separation of a strut and engine from
the airplane during flight.
DATES: This AD is effective June 6, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of June 6, 2011.
ADDRESSES: 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 [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 AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Kenneth Paoletti, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone:
(425) 917-6434; fax (425) 917-6590; e-mail: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
the specified products. That NPRM published in the Federal Register on
November 15, 2010 (75 FR 69612). That NPRM proposed to require an
inspection to determine the part number of the mid-pivot access door
and to determine if the correct door is installed, and the installation
of a marker on the mid-pivot access door, and if necessary, repetitive
ultrasonic inspections for cracking of the mid-pivot bolt assembly and
eventual replacement of the mid-pivot bolt assembly.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Support for the NPRM
Boeing supported the contents of the NPRM.
Request To Include References to Airplane Maintenance Manual
United Airlines (UAL) stated that it is concerned about the actions
in Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010,
being undone and leading to the same condition. UAL suggested that we
revise the NPRM to include airplane maintenance manual (AMM)
references, including a check for marker BAC27EPP667 before installing
the access door. As an alternative, UAL also suggested that the mid-
pivot access door part number could be changed instead of keeping the
same part number. UAL stated that if the NPRM is not changed to
incorporate one of the two options, then the required actions could be
undone if doors without the marker are installed.
We disagree with the request to revise this AD. Section 39.7 of the
Federal Aviation Regulations (14 CFR 39.7) states the following:
``Anyone who operates a product that does not meet the requirements of
an applicable airworthiness directive is in violation of this
section.'' Therefore, operators are prohibited from installing a door
that does not meet the requirements of this AD. However, operators are
permitted to add a check to applicable AMM to prevent installing the
incorrect access door. We have not changed the final rule in regard to
this issue.
Request To Clarify Figures in Service Information
UPS requested that we clarify the figures C-C and D-D on sheets 7
and 8 of Appendix B of Boeing Alert Service Bulletin 747-54A2232, dated
April 15, 2010. UPS stated that the transducer
[[Page 24350]]
positions `A' and `B' on sheet 7 of Appendix B do not coincide with the
transducer positions `A' and `B' on the cross-sections C and D on sheet
8 of Appendix B.
We agree to clarify. Both sheets show the transducer in position
`A' over the grease channel, and the transducer in position `B'
adjacent to the grease channel. Sheet 7 provides a top-down view on the
mid-pivot pin, and sheet 8 is a side view with the grease channel in a
single location for both views. The side view on sheet 8 is only
intended to show which end of the pin is correct. No change to the
service bulletin or rule is needed. We have not changed the final rule
in regard to this issue.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
We estimate that this AD affects 95 airplanes of U.S. registry. We
also estimate that it would take about 3 work-hours per product to
comply with this AD. The average labor rate is $85 per work-hour. Based
on these figures, we estimate the cost of this AD to the U.S. operators
to be $24,225, or $255 per product.
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
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):
2011-09-14 The Boeing Company: Amendment 39-16676; Docket No. FAA-
2010-1111; Directorate Identifier 2010-NM-129-AD.
Effective Date
(a) This AD is effective June 6, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 747-200B, -300,
-400, -400D, and -400F series airplanes; certificated in any
category; equipped with Pratt and Whitney 4000 or General Electric
CF6-80C2 series engines, as identified in Boeing Alert Service
Bulletin 747-54A2232, dated April 15, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/pylons.
Unsafe Condition
(e) This AD was prompted by a report that the left and right
access doors of the spring beam mid-pivot bolt assembly for the No.
1 strut were inadvertently installed in the incorrect position
during strut modification. The Federal Aviation Administration is
issuing this AD to detect and correct incorrectly installed mid-
pivot bolt assemblies on the spring beam on the outboard struts.
Incorrectly installed bolt assemblies could lead to fatigue cracking
and consequent fracturing of the mid-pivot bolt assembly, which
could lead to loss of the spring beam load path and the possible
separation of a strut and engine from the airplane during flight.
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.
Inspection To Determine if Correct Door Is Installed
(g) Within 24 months after the effective date of this AD, do an
inspection to determine if the correct mid-pivot access door is
installed, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010.
(h) If, during the inspection required by paragraph (g) of this
AD, the correct mid-pivot door is found to be installed, before
further flight, install a marker on the mid-pivot access door, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-54A2232, dated April 15, 2010.
(i) If, during the inspection required by paragraph (g) of this
AD, the correct mid-pivot door is not found to be installed, before
further flight, do the actions required by paragraphs (i)(1),
(i)(2), and (i)(3) of this AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-54A2232, dated
April 15, 2010.
(1) Rotate the mid-pivot bolt assembly to the correct
orientation and replace the mid-pivot access door with a new or
serviceable mid-pivot access door.
(2) Install a marker on the mid-pivot access door.
(3) Do the actions required by paragraph (i)(3)(i) or (i)(3)(ii)
of this AD.
(i) (Option 1) Do an ultrasonic inspection for cracking of the
mid-pivot bolt assembly.
(A) If no cracking is found, do the actions required by
paragraphs (i)(3)(i)(A)(1) and (i)(3)(i)(A)(2) of this AD.
(1) Repeat the ultrasonic inspection for cracking of the mid-
pivot bolt assembly thereafter at intervals not to exceed 24 months
until the action required by paragraph (i)(3)(i)(A)(2) of this AD is
done.
(2) Within 60 months after the effective date of this AD,
replace the mid-pivot bolt assembly with a new mid-pivot bolt
assembly. Replacement terminates the repetitive inspections required
by paragraph (i)(3)(i)(A)(1) of this AD.
(B) If any cracking is found, replace the mid-pivot bolt
assembly with a new mid-pivot bolt assembly, before further flight.
(ii) (Option 2) Replace the mid-pivot bolt assembly with a new
mid-pivot bolt assembly.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the
[[Page 24351]]
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: [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.
Related Information
(k) For more information about this AD, contact Kenneth
Paoletti, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 917-6434; fax (425)
917-6590; [email protected].
Material Incorporated by Reference
(l) You must use Boeing Alert Service Bulletin 747-54A2232,
dated April 15, 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 Boeing Alert Service Bulletin 747-
54A2232, dated April 15, 2010, 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
[email protected]; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information at the FAA,
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.
Issued in Renton, Washington, on April 15, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-9919 Filed 4-29-11; 8:45 am]
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