[Federal Register Volume 71, Number 109 (Wednesday, June 7, 2006)]
[Rules and Regulations]
[Pages 32818-32822]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-5125]


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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