[Federal Register Volume 73, Number 43 (Tuesday, March 4, 2008)]
[Rules and Regulations]
[Pages 11534-11536]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-3749]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0204; Directorate Identifier 2007-NM-083-AD; 
Amendment 39-15397; AD 2008-05-03]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, 
-200B, -200C, -200F, -300, 747SP, and 747SR Series Airplanes Powered by 
General Electric (GE) CF6-45/50 and Pratt & Whitney (P&W) JT9D-70, 
JT9D-3 or JT9D-7 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 certain 
Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, 
747SP, and 747SR series airplanes powered by General Electric (GE) CF6-
45/50 and Pratt & Whitney (P&W) JT9D-70, JT9D-3, or JT9D-7 series 
engines. This AD requires repetitive inspections to find cracks and 
broken fasteners of the rear engine mount bulkhead of the inboard and 
outboard nacelle struts, and repair if necessary. For certain 
airplanes, this AD mandates a terminating modification for certain 
inspections of the inboard and outboard nacelle struts. This AD results 
from reports of web and frame cracks and sheared attachment fasteners 
on the inboard and outboard nacelle struts. We are issuing this AD to 
detect and correct cracks and broken fasteners of the inboard and 
outboard nacelle struts, which could result in possible loss of the 
rear engine mount bulkhead load path and consequent separation of the 
engine from the airplane.

DATES: This AD is effective April 8, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 8, 
2008.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.

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 (telephone 800-647-5527) is the 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: Tamara Anderson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6421; fax (425) 917-6590.

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 
certain Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, -
300, 747SP, and 747SR series airplanes powered by General Electric (GE) 
CF6-45/50 and Pratt & Whitney (P&W) JT9D-70, JT9D-3, or JT9D-7 series 
engines. That NPRM was published in the Federal Register on November 
19, 2007 (72 FR 64961). That NPRM proposed to require repetitive 
inspections to find cracks and broken fasteners of the rear engine 
mount bulkhead of the inboard and outboard nacelle struts, and repair 
if necessary. For certain airplanes, that NPRM proposed to mandate a 
terminating modification for certain inspections of the inboard and 
outboard nacelle struts.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Boeing supports the NPRM.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    There are about 460 airplanes of the affected design in the 
worldwide fleet. This AD affects about 135 airplanes of U.S. registry.
    It takes about 4 work hours per airplane to accomplish the required 
detailed inspection, at an average labor rate of $80 per work hour. 
Based on these figures, the estimated cost of the required inspection 
is $43,200, or $320 per airplane, per inspection cycle.
    It takes about 32 work hours per airplane to accomplish the 
required high frequency eddy current inspection, at an average labor 
rate of $80 per work hour. Based on these figures, the estimated cost 
of the required high frequency eddy current inspection is $345,600, or 
$2,560 per airplane, per inspection cycle.
    For Groups 1, 2, and 5 airplanes, it takes between approximately 10 
and 95 work hours per strut (four struts per airplane) to accomplish 
the required modification, depending on airplane configuration, at an 
average labor rate of $80 per work hour. Parts cost for the

[[Page 11535]]

fasteners is between $269 and $897 per strut. Based on these figures, 
the cost impact of the required modification is between $4,276 and 
$33,988 per airplane. We are unable to provide specific information as 
to the cost of the actual parts other than the fasteners that are 
required to accomplish the required modification since the parts will 
be supplied from operator stock.

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:

2008-05-03 Boeing: Amendment 39-15397. Docket No. FAA-2007-0204; 
Directorate Identifier 2007-NM-083-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective April 8, 
2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model 747-100, -100B, -100B SUD,--200B,--
200C, -200F, -300, 747SP, and 747SR series airplanes; certificated 
in any category; powered by General Electric (GE) CF6-45/50 and 
Pratt & Whitney (P&W) JT9D-70, JT9D-3, or JT9D-7 series engines; as 
identified in Boeing Alert Service Bulletin 747-54A2202, Revision 1, 
dated June 22, 2006.

Unsafe Condition

    (d) This AD results from reports of web and frame cracks and 
sheared attachment fasteners on the inboard and outboard nacelle 
strut. We are issuing this AD to detect and correct cracks and 
broken fasteners of the inboard and outboard nacelle struts, which 
could result in possible loss of the rear engine mount bulkhead load 
path and consequent separation of the 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.

Compliance Times

    (f) Do all applicable actions specified in paragraphs (g), (h), 
and (i) of this AD at the applicable times specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-54A2202, 
Revision 1, dated June 22, 2006, except that where paragraph 1.E. of 
the service bulletin specifies starting the compliance time from ``* 
* * the release date of Revision 1 of this service bulletin,'' this 
AD requires starting the compliance time from the effective date of 
this AD.

Initial and Repetitive Inspections/Corrective Actions

    (g) For all airplanes: Perform detailed and high frequency eddy 
current inspections for cracks and broken fasteners of the rear 
engine mount bulkhead of the inboard and outboard nacelle struts, 
and do all applicable related investigative and corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-54A2202, Revision 1, dated June 22, 2006. 
Repeat the applicable inspection and actions thereafter at the 
applicable interval specified in paragraph 1.E., ``Compliance,'' of 
the service bulletin. Accomplishing the applicable repair (Repair 1, 
2, 3, or 4, or repair per the Boeing 747 Structural Repair Manual, 
Section 54-11-03 or 54-12-03) terminates the requirements in this 
paragraph for that nacelle strut only.

Modification

    (h) For Groups 1, 2, and 5 airplanes: Do the applicable 
modification (Repair 2, 3, or 4) of the rear engine mount bulkhead 
of the inboard and outboard nacelle struts, and all the applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
54A2202, Revision 1, dated June 22, 2006. Accomplishing this 
modification terminates the requirements in paragraph (g) of this AD 
for that nacelle strut only.

Post-Modification Inspection/Corrective Actions

    (i) For Groups 1, 2, and 5 airplanes on which the applicable 
corrective actions (Repair 1, 2, 3, or 4) required by paragraph (g) 
of this AD have been accomplished; or the applicable modification 
(Repair 2, 3, or 4) required by paragraph (h) of this AD has been 
accomplished: At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-54A2202, 
Revision 1, dated June 22, 2006, or within 6 months after the 
effective date of this AD, whichever occurs later, perform detailed 
and high frequency eddy current inspections for cracks and broken 
fasteners of the rear engine mount bulkhead of the inboard and 
outboard nacelle struts, and do all applicable related investigative 
and corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-54A2202, Revision 
1, dated June 22, 2006. Repeat the applicable inspections and 
actions thereafter at the applicable interval specified in paragraph 
1.E., ``Compliance,'' of the service bulletin.

Exception to Service Bulletin

    (j) If any crack or any broken fastener is found during any 
inspection required by this AD, and Boeing Alert Service Bulletin 
747-54A2202, Revision 1, dated June 22, 2006, specifies to contact 
Boeing for appropriate action: Before further flight, repair the 
discrepancy using a method approved in accordance with the 
procedures specified in paragraph (k) of this AD.

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) To request a different method of compliance or a different 
compliance time

[[Page 11536]]

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 
appropriate principal inspector (PI) in the FAA Flight Standards 
District Office (FSDO), or lacking a PI, your local FSDO.
    (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

    (l) You must use Boeing Alert Service Bulletin 747-54A2202, 
Revision 1, dated June 22, 2006, 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, P.O. Box 3707, Seattle, Washington 
98124-2207.
    (3) You may review copies of the service information 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on February 20, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-3749 Filed 3-3-08; 8:45 am]
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