[Federal Register: November 19, 2007 (Volume 72, Number 222)]
[Proposed Rules]
[Page 64961-64964]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19no07-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0204; Directorate Identifier 2007-NM-083-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD,
-200B, -200C, -200F, -300, 747SP, and 747SR Series Airplanes Powered by
General Electric (GE) CF6-45/50 and Pratt & Whitney (P&W) JT9D-70,
JT9D-3 or JT9D-7 Series Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -
200F, -300, 747SP, and 747SR series airplanes powered by General
Electric (GE) CF6-45/50 and Pratt & Whitney (P&W) JT9D-70, JT9D-3 or
JT9D-7 series engines. This proposed AD would require repetitive
inspections to find cracks and broken fasteners of the rear engine
mount bulkhead of the inboard and outboard nacelle struts, and repair
if necessary. For certain airplanes, this proposed AD mandates a
terminating modification for certain inspections of the inboard and
outboard nacelle struts. This proposed AD results from reports of web
and frame cracks and sheared attachment fasteners on the inboard and
outboard nacelle struts. We are proposing this AD to detect and correct
cracks and broken fasteners of the inboard and outboard nacelle struts,
which could result in possible loss of the rear engine mount bulkhead
load path and consequent separation of the engine from the airplane.
DATES: We must receive comments on this proposed AD by January 3, 2008.
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.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6421; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
0204; Directorate Identifier 2007-NM-083-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light 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
with FAA personnel concerning this proposed AD. Using the search
function of that Web site, anyone can find and read the comments in any
of our dockets, including the name of the individual who sent the
comment (or signed the comment on behalf of an association, business,
labor union, etc.). You may review DOT's complete Privacy Act Statement
in the Federal Register published on April 11, 2000 (65 FR 19477-78),
or you may visit http://www.regulations.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday,
[[Page 64962]]
except Federal holidays. The Docket Operations office (telephone (800)
647-5527) is located on the ground floor of the West Building at the
DOT street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
On January 2, 2002, the FAA issued a notice of proposed rulemaking
(NPRM), Docket No. 2001-NM-40-AD, to address the identified unsafe
condition; that action was published in the Federal Register on January
9, 2002 (67 FR 1167). That NPRM proposed to require repetitive
inspections to find cracks and broken fasteners of the inboard and
outboard nacelle struts of the rear engine mount bulkhead, and repair
if necessary. For certain airplanes, that NPRM provided for an optional
terminating modification for the inspections of the outboard nacelle
struts. That NPRM was prompted by reports indicating that fatigue
cracking of the inboard and outboard nacelle struts of the rear engine
mount bulkhead was found. The unsafe condition is cracks and broken
fasteners of the inboard and outboard nacelle struts. Subsequently, we
worked with the manufacturer to ensure that the unsafe condition is
adequately addressed and appropriate service instructions are
available. We have also received many new reports of additional web and
frame cracks and sheared attachment fasteners, and reports of cracks on
the outboard struts of airplanes not identified in the applicability of
that NPRM. In addition, we have considered comments submitted in
response to that NPRM.
In light of all this information, we have determined that the
corrective actions required by that NPRM are inadequate for addressing
the identified unsafe condition; therefore, we have withdrawn that NPRM
and are issuing this new proposed AD to address the unsafe condition.
Relevant Service Information
In light of those new reports, Boeing has issued Alert Service
Bulletin 747-54A2202, Revision 1, dated June 22, 2006. The original
issue, dated December 21, 2000, was referred to in the NPRM, Docket No.
2001-NM-40-AD, as the appropriate source of service information for
accomplishing certain actions. Revision 1 includes the following
changes to the original issue:
Adds additional airplanes powered by General Electric (GE)
CF6-45/50 series engines to the effectivity (identified as Group 6
airplanes).
Adds modifications, inspections, and post-modification
inspections for airplanes in Groups 1 through 5 (those included in the
effectivity of the original issue of the service bulletin).
Adds outboard strut inspections for Groups 3, 4, and 5
airplanes included in the effectivity of the original issue of the
service bulletin.
The compliance times listed in the Part A Inspections, as specified
in the service bulletin, are as follows: The compliance time for
airplanes on which the detailed visual and high frequency eddy current
(HFEC) inspections of the inboard and outboard strut rear engine mount
bulkheads in the original issue of the service bulletin have been done
ranges from 180 days to 18 months from the release date of Revision 1
of the service bulletin or 350 flight cycles to 1,200 flight cycles,
whichever occurs earlier; the repetitive interval ranges from 350
flight cycles to 1,200 flight cycles or 18 months, whichever occurs
earlier.
The compliance time for airplanes on which the inspections in the
original issue of the service bulletin have not been done is within 90
days from the release date of Revision 1 of the service bulletin to
within 18 months or 1,200 flight cycles, whichever occurs earlier; the
repetitive interval ranges from 350 flight cycles to 1,200 flight
cycles or 18 months, whichever occurs earlier. The compliance times
depend on airplane configuration and nacelle strut position.
The compliance times listed in the Part B Inspections--Post
Modification, as specified in the service bulletin, are as follows: The
compliance time for airplanes on which the repairs have been done
ranges from 600 flight cycles to 7,200 flight cycles or 18 months after
repair; the repetitive interval ranges from 600 flight cycles to 1,200
flight cycles or 18 months, whichever occurs earlier. At 7,200 flight
cycles after repair the repetitive interval changes from doing a
detailed visual inspection every 1,200 flight cycles or 18 months, to
doing detailed visual and HFEC inspections every 1,200 flight cycles or
18 months.
Depending on the group, the service bulletin specifies doing the
following repairs, related investigative actions, and corrective
actions:
For Groups 1, 2, and 5 airplanes (on inboard struts only
for Group 5): If any crack is found, do Repair 1 of the service
bulletin. Replace cracked frames with new frames, and install repair
doublers, chords, and corrosion resistant steel (CRES) repair angles
before further flight. Repair 1 includes the following related
investigative and corrective actions: Detailed visual and HFEC
inspections for cracks of the bulkhead frame, replacement of cracked
frames, inspection of holes in frames for cracks, inspection of holes
in chords for cracks, replacement of cracked chords, inspection of
holes in frame and skin for cracks, contacting Boeing for repair for
cracks in skin, inspection of holes on aft left-hand and right-hand
sides of bulkhead in frame and skin for cracks, inspection of frame
edge for cracks, and inspection of the holes on the forward side of
bulkhead in frame and skin for cracks.
For Groups 1 and 5 airplanes (on inboard struts only for
Group 5): If more than two broken fasteners are found, do Repair 2 or 3
of the service bulletin (depending on configuration). Install doublers,
chords, and CRES repair angles before further flight.
--Repair 2 includes the following related investigative and
corrective actions: Detailed visual and HFEC inspections for cracks of
the bulkhead frame, repair or replacement of cracked frames, inspection
of holes in frames for cracks, inspection of holes in chords for
cracks, replacement of cracked chords, inspection of holes on aft left-
hand and right-hand sides of bulkhead in frame and skin for cracks,
inspection of frame edge for cracks, and inspection of the holes on the
forward side of bulkhead in frame and skin for cracks.
--Repair 3 includes the following related investigative and
corrective actions: Inspection of holes in frames for cracks,
replacement of cracked frames, inspection of frame edge for cracks, and
replacement of cracked frames.
For Group 1 airplanes: If any new crack, extension of
stop-drilled crack, or more than two broken fasteners are found, do
Repair 4 of the service bulletin. Install additional CRES repair angles
before further flight. Repair 4 includes the following related
investigative and corrective actions: HFEC inspections of the fastener
holes and open holes of the bulkhead frame for cracks, stop drill or
trim out cracks found in the frame only, contact Boeing for repair of
cracks in the existing doubler or repair angle, and fabricate and
install certain repair angles.
For Groups 1, 2, and 5 airplanes: If only one or two
broken fasteners are found, do Repair 5 of the service bulletin,
replace the fasteners before further flight, and do Repair 2, 3, or 4,
depending on configuration, within 18 or 36 months from the release
date of the service bulletin, as applicable. Repair 5 includes the
following related investigative and corrective actions:
[[Page 64963]]
HFEC inspections of the fastener holes for cracks, and repair of any
cracks.
For Groups 3, 4, and 6 airplanes: If any crack, or more
than two broken fasteners are found, do the applicable repair before
further flight (contact Boeing or repair per the structural repair
manual, depending on configuration).
For Groups 3, 4, and 6 airplanes: If only one or two
broken fasteners are found, do Repair 5 of the service bulletin before
further flight.
For Group 5 airplanes (outboard strut only): If any crack
or broken fastener is found, repair and contact Boeing before further
flight.
For airplanes that have done post-modification
inspections: If any crack or broken fastener is found, repair and
contact Boeing before further flight.
The procedures in the service bulletin specify doing the following
modifications for Groups 1, 2, and 5 airplanes, depending on airplane
configuration:
If no crack or broken fastener is found, do Repair 2 or 3
within 18 to 36 months.
If no new crack, extension of stop drill cracking, or
broken fastener is found, do Repair 4 within 36 months.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously, except as discussed below.
Differences Between the Alert Service Bulletin and This Proposed AD
The alert service bulletin 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 an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Clarification of Inspection Terminology
In this NPRM, the ``detailed visual inspection'' specified in
Boeing Alert Service Bulletin 747-54A2202, Revision 1, is referred to
as a ``detailed inspection.''
Costs of Compliance
There are about 460 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 135 airplanes of
U.S. registry.
It would take about 4 work hours per airplane to accomplish the
proposed detailed inspection, at an average labor rate of $80 per work
hour. Based on these figures, the estimated cost of the proposed
inspection is $43,200, or $320 per airplane, per inspection cycle.
It would take about 32 work hours per airplane to accomplish the
proposed high frequency eddy current inspection, at an average labor
rate of $80 per work hour. Based on these figures, the estimated cost
of the proposed high frequency eddy current inspection is $345,600, or
$2,560 per airplane, per inspection cycle.
For Groups 1, 2, and 5 airplanes, it would take between
approximately 10 and 95 work hours per strut (four struts per airplane)
to accomplish the proposed modification, depending on airplane
configuration, at an average labor rate of $80 per work hour. Parts
cost for the fasteners only would be between $269 and $897 per strut.
Based on these figures, the cost impact of the proposed modification
would be between $4,276 and $33,988 per airplane. We are unable to
provide specific information as to the cost of the actual parts other
than the fasteners that would be required to accomplish the proposed
modification since the parts would be supplied from operator stock.
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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2007-0204; Directorate Identifier 2007-NM-
083-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
3, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 747-100, -100B, -100B SUD, 200B,
200C, -200F, -300, 747SP, and 747SR series airplanes; certificated
in any category; powered by General Electric (GE) CF6-45/50 and
Pratt & Whitney (P&W) JT9D-70, JT9D-3 or JT9D-7 series engines; as
identified in Boeing Alert Service Bulletin 747-54A2202, Revision 1,
dated June 22, 2006.
[[Page 64964]]
Unsafe Condition
(d) This AD results from reports of web and frame cracks and
sheared attachment fasteners on the inboard and outboard nacelle
strut. We are issuing this AD to detect and correct cracks and
broken fasteners of the inboard and outboard nacelle struts, which
could result in possible loss of the rear engine mount bulkhead load
path and consequent separation of the engine from the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Compliance Times
(f) Do all applicable actions specified in paragraphs (g), (h),
and (i) of this AD at the applicable times specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2202,
Revision 1, dated June 22, 2006, except that where paragraph 1.E. of
the service bulletin specifies starting the compliance time from ``*
* * the release date of Revision 1 of this service bulletin,'' this
AD requires starting the compliance time from the effective date of
this AD.
Initial and Repetitive Inspections/Corrective Actions
(g) For all airplanes: Perform detailed and high frequency eddy
current inspections for cracks and broken fasteners of the rear
engine mount bulkhead of the inboard and outboard nacelle struts,
and do all applicable related investigative and corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006.
Repeat the applicable inspection and actions thereafter at the
applicable interval specified in paragraph 1.E., ``Compliance,'' of
the service bulletin. Accomplishing the applicable repair (Repair 1,
2, 3, or 4, or repair per the 747 structural repair manual, section
54-11-03 or 54-12-03) terminates the requirements in this paragraph
for that nacelle strut only.
Modification
(h) For Groups 1, 2, and 5 airplanes: Do the applicable
modification (Repair 2, 3, or 4) of the rear engine mount bulkhead
of the inboard and outboard nacelle struts, and all the applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2202, Revision 1, dated June 22, 2006. Accomplishing this
modification terminates the requirements in paragraph (g) of this AD
for that nacelle strut only.
Post-Modification Inspection/Corrective Actions
(i) For Groups 1, 2, and 5 airplanes on which the applicable
corrective actions (Repair 1, 2, 3, or 4) required by paragraph (g)
of this AD have been accomplished; or the applicable modification
(Repair 2, 3, or 4) required by paragraph (h) of this AD has been
accomplished: At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2202,
Revision 1, dated June 22, 2006, or within 6 months after the
effective date of this AD, whichever occurs later, perform detailed
and high frequency eddy current inspections for cracks and broken
fasteners of the rear engine mount bulkhead of the inboard and
outboard nacelle struts, and do all applicable related investigative
and corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-54A2202, Revision
1, dated June 22, 2006. Repeat the applicable inspections and
actions thereafter at the applicable interval specified in paragraph
1.E., ``Compliance,'' of the service bulletin.
Exception to Service Bulletin
(j) If any crack or any broken fastener is found during any
inspection required by this AD, and Boeing Alert Service Bulletin
747-54A2202, Revision 1, dated June 22, 2006, specifies to contact
Boeing for appropriate action: Before further flight, repair the
discrepancy using a method approved in accordance with the
procedures specified in paragraph (k) of this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(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 appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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 an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who 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 November 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-22542 Filed 11-16-07; 8:45 am]
BILLING CODE 4910-13-P