AD 2010-14-09

[Federal Register Volume 75, Number 127 (Friday, July 2, 2010)]
[Rules and Regulations]
[Pages 38404-38406]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2010-16046]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0641; Directorate Identifier 2010-NM-130-AD; 
Amendment 39-16354; AD 2010-14-09]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747-100B, 747-
200B, 747-200F, 747-300, 747-400, 747-400F, and 747SP Series Airplanes 
Equipped with Rolls-Royce RB211-524 Series Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Model 747-100B, 747-200B, 747-200F, 747-300, 747-400, 747-400F, and 
747SP series airplanes. This AD requires repetitive detailed and high 
frequency eddy current inspections of the forward and aft sides of the 
strut front spar chord for cracks and fractures at each strut location, 
and corrective actions if necessary. This AD results from reports of 
cracks and fractures in the nacelle strut front spar chord assembly. We 
are issuing this AD to detect and correct cracks and fractures of the 
nacelle strut front spar chord assembly. Fracture of the front spar 
chord assembly could lead to loss of the strut upper link load path and 
consequent fracture of the diagonal brace, which could result in in-
flight separation of the strut and engine from the airplane.

DATES: This AD is effective July 19, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of July 19, 
2010.
    We must receive comments on this AD by August 16, 2010.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 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 <a href="/cdn-cgi/l/email-protection#39545c175b565c5a5654795b565c50575e175a5654"><span class="__cf_email__" data-cfemail="0469612a666b61676b6944666b616d6a632a676b69">[email&#160;protected]</span></a>; Internet 
<a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 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: Ken Paoletti, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6434; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received a report that an operator found a cracked strut 
number 2 upper chord on a Rolls-Royce-powered airplane while 
accomplishing the actions specified in Boeing Service Bulletin 747-54-
2213. The upper chord was 50 percent cracked and had to be replaced. 
The airplane had accumulated approximately 10,500 total flight cycles 
and 83,700 total flight hours.
    In addition, two other operators reported finding two cracks on two 
Rolls-Royce RB211-powered airplanes on the strut number 1 upper chord. 
Both cracks were repaired and neither upper chord had to be replaced. 
The upper chords on these two airplanes had accumulated approximately 
9,300 and 16,100 total flight cycles and 78,100 and 56,700 total flight 
hours respectively.
    This condition, if not corrected, could result in the loss of the 
strut upper link load path. Continued operation without the strut upper 
link load path could result in the fracture of the diagonal brace, and 
subsequent separation of the strut and engine from the airplane during 
flight.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-54A2224, Revision 3, 
dated May 20, 2010. Revision 3 of this service bulletin was issued, 
among other reasons, to add Model 747-100B, 747-200B, 747-200F, 747-
300, 747-400, 747-400F, and 747SP equipped with Rolls-Royce RB211-524 
series engines. This service bulletin describes procedures for 
repetitive detailed inspections and high frequency eddy current (HFEC) 
inspections of the forward and aft sides of the strut front spar chord 
assemblies for cracks and fractures at each strut location, and 
corrective actions if necessary. Corrective actions include contacting 
Boeing for additional instructions if any crack or fracture is found, 
and repairing any cracks and fractures.

Other Related Rulemaking

    On December 30, 2009, we issued AD 2010-01-10, Amendment 39-16168 
(75 FR 3150, January 20, 2010), applicable to certain Model 747-100, 
747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, 
and 747SP series airplanes equipped with General Electric (GE) CF6-45 
or -50 series engines, or equipped with Pratt & Whitney JT9D-3 or -7 
(excluding -70) series engines. That AD currently requires repetitive 
inspections to detect cracks and fractures of the strut front spar 
chord assembly (including the forward side) at each strut location, and

[[Page 38405]]

repair if necessary. That AD requires a one-time inspection for 
cracking of the forward side of the front spar chord assembly on the 
inboard and outboard struts, installation of a cap skin doubler for 
certain airplanes, and repair if necessary. Certain actions provided in 
that AD terminate the repetitive inspections of the forward side of the 
strut front spar chord assembly; the inspections of the aft side 
assembly are not terminated and continue to be required. That AD 
referred to Boeing Alert Service Bulletin 747-54A2224, Revision 1, 
dated November 16, 2006, to address the identified unsafe condition on 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 
747-300, 747SR, and 747SP series airplanes equipped with GE CF6-45 or -
50 series engines, or equipped with Pratt & Whitney JT9D-3 or -7 
(excluding -70) series engines.

FAA's Determination and Requirements of This AD

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs. This AD requires accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between the AD and the Service Information.''

Differences Between the AD and the Service Information

    Boeing Alert Service Bulletin 747-54A2224, Revision 3, dated May 
20, 2010, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this AD would require repairing those 
conditions in one of the following ways:
    <bullet> In accordance with a method that we approve; or
    <bullet> Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we might consider further rulemaking then.

FAA's Justification and Determination of the Effective Date

    Continued operation without the strut upper link load path could 
result in the fracture of the diagonal brace, and subsequent separation 
of the strut and engine from the airplane during flight. Because of our 
requirement to promote safe flight of civil aircraft and thus, the 
critical need to assure structural integrity of the engine support 
structure and the short compliance time involved with this action, this 
AD must be issued immediately.
    Because an unsafe condition exists that requires the immediate 
adoption of this AD, we find that notice and opportunity for prior 
public comment hereon are impracticable and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2010-0641; Directorate Identifier 2010-NM-130-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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), 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.

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

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 AD:

2010-14-09 The Boeing Company: Amendment 39-16354. Docket No. FAA-
2010-0641; Directorate Identifier 2010-NM-130-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective July 19, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 747-100B, 747-
200B, 747-200F, 747-300, 747-400, 747-400F, and 747SP series 
airplanes; certificated in any category; equipped with Rolls-Royce 
RB211-524 series engines; as identified in Boeing Alert Service 
Bulletin 747-54A2224, Revision 3, dated May 20, 2010.

[[Page 38406]]

Subject

    (d) Air Transport Association (ATA) of America Code 54: 
Nacelles/Pylons.

Unsafe Condition

    (e) This AD results from reports of cracks and fractures in the 
nacelle strut front spar chord assembly. The Federal Aviation 
Administration is issuing this AD to detect and correct cracks and 
fractures of the nacelle strut front spar chord assembly. Fracture 
of the front spar chord assembly could lead to loss of the strut 
upper link load path and consequent fracture of the diagonal brace, 
which could result in in-flight separation of the strut and engine 
from the airplane.

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.

Inspections of the Forward and Aft Sides of the Strut Front Spar Chord 
Assemblies

    (g) Before the accumulation of 8,000 total flight cycles, or 
within 90 days after the effective date of this AD, whichever occurs 
later: Perform a detailed inspection and a high frequency eddy 
current (HFEC) inspection for cracking or fracturing in the forward 
and aft sides of the strut front spar chord, in accordance with 
Parts 1 and 2 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-54A2224, Revision 3, dated May 20, 2010. If no 
cracking or fracturing is found, repeat the inspections thereafter 
at intervals not to exceed 1,500 flight cycles.

Corrective Actions

    (h) If any crack or fracture is found during any inspection 
required by this AD: Before further flight, repair the crack or 
fracture using a method approved in accordance with the procedures 
specified in paragraph (i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle 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: Ken Paoletti, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6434; fax (425) 917-6590. 
Information may be e-mailed to: <a href="/cdn-cgi/l/email-protection#71485c303f3c5c22141005051d145c30323e5c303c3e325c2314000414020502311710105f161e07"><span class="__cf_email__" data-cfemail="c6ffeb87888beb95a3a7b2b2aaa3eb878589eb878b8985eb94a3b7b3a3b5b2b586a0a7a7e8a1a9b0">[email&#160;protected]</span></a>.
    (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.

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 747-54A2224, 
Revision 3, dated May 20, 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 this service information 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 
<a href="/cdn-cgi/l/email-protection#573a327935383234383a173538323e39307934383a"><span class="__cf_email__" data-cfemail="ef828ac18d808a8c8082af8d808a868188c18c8082">[email&#160;protected]</span></a>; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (3) You may review copies of the 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.
    (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 NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on June 21, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-16046 Filed 7-1-10; 8:45 am]
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