Document ID: FAA-2010-1111-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Boeing Co. Model 747-200B, -300, -400, -400D, and -400F Series Airplanes Powered by Pratt and Whitney 4000 or General Electric CF6 80C2 Series Engines
Posted Date: 2010-11-15T05:00Z

[Federal Register Volume 75, Number 219 (Monday, November 15, 2010)]
[Proposed Rules]
[Pages 69612-69614]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-28605]

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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]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Model 747-200B, -300, -400, -400D, and -400F series airplanes. 
This proposed AD would require an inspection to determine the part 
number of the door and to determine if the correct mid-pivot access 
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 proposed AD results from a report that 
the left and right spring beam mid-pivot bolt assembly access doors for 
the No. 1 strut were inadvertently installed in the incorrect position 
during strut modification. We are proposing 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: We must receive comments on this proposed AD by December 30, 
2010.

ADDRESSES: You may send comments by any of the following methods:

[[Page 69613]]

     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, me.boecom@boeing.com; 
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 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: 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.

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-2010-1111; 
Directorate Identifier 2010-NM-129-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

    We have received a report that the mid-pivot access doors on the 
No. 1 strut were inadvertently installed in the incorrect position 
during strut modification. The design of the access doors can allow the 
doors to be installed on either side of the strut. The mid-pivot access 
door has machined tabs that fit the slots in the head of the mid-pivot 
bolt assembly. The machined tabs correctly orient the mid-pivot bolt 
assembly and prevent the mid-pivot bolt from rotating in the spring 
beam. The correct orientation of the mid-pivot bolt reduces the fatigue 
on the cross-drilled lubrication channel. If the lubrication channel is 
not in the correct orientation, fatigue cracking could develop in the 
mid-pivot bolt assembly. The fatigue cracking could lead to the 
fracture of the mid-pivot bolt assembly. Fracture of the mid-pivot bolt 
assembly could result in the loss of the spring beam load path. Loss of 
the spring beam load path could result in the separation of a strut and 
engine from the airplane during flight.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-54A2232, dated 
April 15, 2010. The service bulletin describes procedures for doing an 
inspection to determine the part number of the door and to determine if 
the correct mid-pivot access door is installed. For airplanes on which 
the correct door is installed, the service bulletin describes 
procedures for installing a marker on the mid-pivot access door. For 
airplanes on which the correct access door is not installed, Boeing 
Alert Service Bulletin 747-54A2232, dated April 15, 2010, describes 
procedures for rotating the mid-pivot bolt assembly to the correct 
orientation and replacing the access door, and installing the marker on 
the mid-pivot access door. In addition, for those airplanes without the 
correct door, the service bulletin describes procedures for doing one 
of two options:
     Doing repetitive ultrasonic inspections for cracks of the 
mid-pivot bolt assembly, and if no cracking is found, eventually 
replacing the assembly.
     Replacing the mid-pivot bolt assembly before further 
flight. Replacing the mid-pivot bolt assembly terminates the need for 
repetitive inspections.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs. This proposed AD would require accomplishing the actions 
specified in the service information described previously.

Costs of Compliance

    We estimate that this proposed AD would affect 95 airplanes of U.S. 
registry. We also estimate that it would take about 3 work-hours per 
product to comply with this proposed AD. The average labor rate is $85 
per work-hour. Based on these figures, we estimate the cost of this 
proposed 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

    We 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 this proposed 
regulation:

[[Page 69614]]

    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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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 adding the following new AD:

The Boeing Company: Docket No. FAA-2010-1111; Directorate Identifier 
2010-NM-129-AD.

Comments Due Date

    (a) We must receive comments by December 30, 2010.

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 results from a report that the left and right spring 
beam mid-pivot bolt assembly access doors 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 authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
Attn: 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. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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.

    Issued in Renton, Washington, on November 2, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-28605 Filed 11-12-10; 8:45 am]
BILLING CODE 4910-13-P