Document ID: FAA-2010-1111-0006
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 ElectricCF6 80C2 Series Engines
Posted Date: 2011-05-02T04:00Z

[Federal Register Volume 76, Number 84 (Monday, May 2, 2011)]
[Rules and Regulations]
[Pages 24349-24351]
From the Federal Register Online via the Government Printing 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 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 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: Kenneth.Paoletti@faa.gov.

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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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; kenneth.paoletti@faa.gov.

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 
me.boecom@boeing.com; 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]
BILLING CODE 4910-13-P