[Federal Register: June 7, 2006 (Volume 71, Number 109)]
[Rules and Regulations]
[Page 32818-32822]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07jn06-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24950; Directorate Identifier 2006-NM-036-AD;
Amendment 39-14627; AD 2006-12-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100B, 747-200B, 747-
200F, 747-300, 747-400, 747-400F, and 747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain 747-100B, 747-200B, 747-200F, 747-300, 747-400, 747-400F, and
747SP series airplanes. This AD requires doing inspections of the
midpivot bolt and midpivot bolt access door of the spring beam of the
inboard side of the outboard struts for discrepancies, installing a
placard on the midpivot bolt access door, and applicable corrective
actions if necessary. This AD results from reports indicating that the
midpivot bolt and midpivot bolt access door of the spring beam of the
inboard side of the outboard struts were installed in the incorrect
position. We are issuing this AD to ensure that the subject midpivot
bolts and midpivot bolt access doors are installed in the correct
position. If not installed in the correct position, a midpivot bolt
could be overloaded and crack or fracture, which could result in the
loss of the spring load path and consequent separation of the
associated
[[Page 32819]]
outboard strut and engine from the airplane.
DATES: This AD becomes effective June 22, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of June 22,
2006.
We must receive comments on this AD by August 7, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, 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 service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We have received reports indicating that the midpivot bolt and
midpivot bolt access door of the spring beam of the inboard side of the
outboard struts were installed in the incorrect position on two
airplanes. On one of the airplanes, the midpivot bolts and midpivot
bolt access doors had been installed during accomplishment of the
modification of the nacelle strut and wing structure in accordance with
Boeing Service Bulletin 747-54A2157 (required by AD 95-13-05, amendment
39-9285 (60 FR 33333, June 28, 1995)). Investigation revealed that the
service bulletin specified incorrect part numbers for the midpivot bolt
access doors. In addition, the production installation drawings did not
provide clear instructions for installing the midpivot bolts and
midpivot bolt access doors, which resulted in the discrepancies on the
other airplane.
The midpivot bolt access door is attached to the skin of the
inboard side of the outboard struts. A midpivot bolt access door has
anti-rotation tabs that fit the slots of the midpivot bolt's head. If
any midpivot bolt access door is not installed correctly or if its
anti-rotation tabs are not properly aligned with the slots of the
midpivot bolt's head, the midpivot bolt and its internal lubrication
channel will not be in correct position. When the lubrication channel
is not in the correct position, a midpivot bolt could be overloaded and
crack or fracture. These conditions, if not corrected, could result in
the loss of a spring beam load path and consequent separation of the
associated outboard strut and engine from the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-54A2225, dated
February 16, 2006. The service bulletin describes the inspection
procedures specified in the table below. The service bulletin also
describes procedures for installing a placard on the midpivot bolt
access doors, and doing applicable corrective actions if necessary. The
applicable corrective actions include changing or replacing any
midpivot bolt access door that is damaged or installed in the incorrect
position with a new or serviceable midpivot bolt access door, and under
certain conditions, replacing the midpivot bolt with a new bolt. The
service bulletin specifies the following compliance time depending on
the airplane configuration and accumulated flight cycles:
``Within 24 months from the release date on this service
bulletin or within 90 days from accumulating 8,000 flight cycles from
the accomplishment of SB 747-54A2157, whichever occurs first;''
``Within 24 months from the release on this service
bulletin or within 90 days from accumulating 8,000 total flight cycles,
whichever occurs first;'' or
``Within 90 days from the release date on this service
bulletin.''
Inspections
------------------------------------------------------------------------
Doing-- Of-- For--
------------------------------------------------------------------------
(1) A general visual The midpivot bolt The correct part
inspection. access doors. number, damage
(i.e., wear, nicks,
gouges, elongated
fastener holes, or
cracks), or the
correct position of
its anti-rotation
tabs.
(2) A general visual The anti-rotation Damage (i.e., wear,
inspection. tabs of the nicks, gouges, or
midpivot bolt cracks) or any
access doors. missing tab.
(3) A general visual The midpivot bolts.. Correct position or
inspection. damage (i.e.,
nicks, gouges, or
cracks).
(4) An ultrasonic inspection The midpivot bolts.. Cracks.
------------------------------------------------------------------------
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design that may be
registered in the U.S. at some time in the future. Therefore, we are
issuing this AD to ensure that the subject midpivot bolts and midpivot
bolt access doors are installed in the correct position. If not
installed in the correct position, a midpivot bolt could be overloaded
and crack or fracture, which could result in the loss of the spring
load path and consequent separation of the associated outboard strut
and engine from the airplane. This AD requires accomplishing the
actions specified in the service information described previously,
except as described under ``Difference Between the Proposed AD and
Service Bulletin.''
Difference Between the Proposed Rule and Service Bulletin
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletin describe procedures for
submitting a report of inspection findings to Boeing, this AD will not
require that action.
[[Page 32820]]
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required inspection and installation of a placard
would take about 6 work hours per airplane, at an average labor rate of
$80 per work hour. Based on these figures, the estimated cost of the AD
would be $480 per airplane.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed under the ADDRESSES section. Include ``Docket No. FAA-
2006-24950; Directorate Identifier 2006-NM-036-AD'' at the beginning of
your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the AD that
might suggest a need to modify it.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this 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 the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif 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.
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 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 the 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 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.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-12-03 Boeing: Amendment 39-14627. Docket No. FAA-2006-24950;
Directorate Identifier 2006-NM-036-AD.
Effective Date
(a) This AD becomes effective June 22, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100B, 747-200B, 747-
200F, 747-300, 747-400, 747-400F, and 747SP series airplanes,
certificated in any category; as identified in Boeing Alert Service
Bulletin 747-54A2225, dated February 16, 2006.
Unsafe Condition
(d) This AD results from reports indicating that the midpivot
bolt and midpivot bolt access door of the spring beam of the inboard
side of the outboard struts were installed in the incorrect
position. We are issuing this AD to ensure that the subject midpivot
bolts and midpivot bolt access doors are installed in the correct
position. If not installed in the correct position, a midpivot bolt
could be overloaded and crack or fracture, which could result in the
loss of the spring load path and consequent separation of the
associated outboard strut and 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.
Inspections
(f) Do the inspections specified in Table 1 of this AD at the
applicable compliance time listed in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-54A2225, dated February 16,
2006; except, where the service bulletin specifies a compliance time
from the release date of the service bulletin, this AD requires
compliance within the specified compliance time after the effective
[[Page 32821]]
date of this AD. Do the inspections in accordance with the
Accomplishment Instructions of the service bulletin.
Table 1.--Inspections
------------------------------------------------------------------------
Do-- Of-- For--
------------------------------------------------------------------------
(1) A general visual The midpivot bolt The correct part
inspection. access doors. number, damage
(i.e., wear, nicks,
gouges, elongated
fastener holes, or
cracks), or the
correct position of
its anti-rotation
tabs.
(2) A general visual The anti-rotation Damage (i.e., wear,
inspection. tabs of the nicks, gouges, or
midpivot bolt cracks) or any
access doors. missing tab.
(3) A general visual The midpivot bolts.. Correct position or
inspection. damage (i.e.,
nicks, gouges, or
cracks).
(4) An ultrasonic inspection The midpivot bolts.. Cracks.
------------------------------------------------------------------------
Note 1: There is a discrepancy in Step 2 of Figure 13, Sheet 2,
of Boeing Alert Service Bulletin 747-54A2225, dated February 16,
2006. The ``MORE DATA'' column of the table incorrectly describes
the anti-rotation slot installation as being ``horizontal and are
perpendicular to the strut skin aft edge.'' The correct description
is ``vertical and are parallel to the strut skin aft edge.''
Installation of a Placard and Corrective Actions
(g) Before further flight after doing the inspections required
by paragraph (f) of this AD, do the applicable actions specified in
Table 2 of this AD in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-54A2225, dated
February 16, 2006.
Table 2.--Installation of A Placard and Corrective Actions
------------------------------------------------------------------------
If-- And if-- Then--
------------------------------------------------------------------------
(1) Any midpivot bolt access Its anti-rotation Install a placard on
door has the correct part tabs are present, the midpivot access
number and no damage. are in the correct door.
position, and have
no damage.
(2) Any midpivot bolt access Its anti-rotation Change the midpivot
door has the incorrect part tabs are present, access door or
number and no damage. are in the replace it with a
incorrect position, new or serviceable
and have no damage. access door, and
install a placard
on the midpivot
access door.
(3) Any midpivot bolt access None................ Replace the midpivot
door has the incorrect part access door with a
number, any damage, or any new or serviceable
damaged or missing anti- door and install a
rotation tab. placard on the
door.
(4) Any midpivot bolt is in It has no damage.... No further action is
the correct position. required by this
paragraph.
(5) Any midpivot bolt is in It has no damage.... Correct the midpivot
the incorrect position. bolt position.
Any midpivot bolt has any None................ Replace the midpivot
damage. bolt with a new
bolt.
------------------------------------------------------------------------
Replacement of Midpivot Bolt
(h) If any condition in paragraph (h)(1) or (h)(2) of this AD is
found on any outboard strut, within 24 months after doing the
inspections required by paragraph (f) of this AD, replace the
midpivot bolt of the spring beam of the inboard side of that
outboard strut with a new midpivot bolt, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2225, dated February 16, 2006.
(1) If any midpivot bolt access door of the spring beam of the
inboard side of the outboard struts is found in the incorrect
position (i.e., the midpivot bolt access door has the incorrect part
number or its anti-rotation tabs are in the incorrect position) and
if no damage is found on that bolt during any inspection required by
paragraph (f) of this AD.
(2) If any midpivot bolt of the spring beam of the inboard side
of the outboard struts is found in the incorrect position and if no
damage is found on that bolt during any inspection required by
paragraph (f) of this AD.
Parts Installation
(i) As of the effective date of this AD, no person may install,
on any airplane, a midpivot access door, part number 65B89670-339,
65B89670-340, 654U6624-356, or 654U6624-357, unless it has been
inspected in accordance with paragraphs (f)(1) and (f)(2) of this AD
and found to have the correct part number for the door location, no
damage, and no damaged or missing anti-rotation tab.
No Reporting
(j) Although the service bulletin referenced in this AD
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
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) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
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 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.
Material Incorporated by Reference
(1) You must use Boeing Alert Service Bulletin 747-54A2225,
dated February 16, 2006, to perform the actions that are required by
this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, WA
98124-2207, for a copy of this service information. You may review
copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the
[[Page 32822]]
Internet at http://dms.dot.gov; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at the NARA, 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 May 26, 2006.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5125 Filed 6-6-06; 8:45 am]
BILLING CODE 4910-13-P