

[Federal Register: December 10, 2007 (Volume 72, Number 236)]
[Rules and Regulations]               
[Page 69590-69591]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10de07-9]                         


[[Page 69590]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28620; Directorate Identifier 2007-NM-090-AD; 
Amendment 39-15299; AD 2007-25-17]
RIN 2120-AA64

 
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD 
requires repetitive inspections for cracking of the station (STA) 1241 
bulkhead fittings just above the canted pressure deck; a one-time 
determination of the edge margin at seven fastener positions on each 
side of the airplane; and related investigative/corrective actions if 
necessary. This AD results from a report that an operator found a 1.65-
inch crack on the STA 1241 bulkhead fitting on the left side of a 
Boeing Model 747-200F series airplane that had accumulated 17,332 total 
flight cycles. We are issuing this AD to detect and correct cracking in 
the STA 1241 bulkhead fittings, which could result in reduced 
structural integrity of the airplane.

DATES: This AD becomes effective January 14, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 14, 
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: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, WA 98057-3356; telephone (425) 917-6437; fax (425) 
917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Boeing Model 
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 
747SR, and 747SP series airplanes. That NPRM was published in the 
Federal Register on July 9, 2007 (72 FR 37130). That NPRM proposed to 
require repetitive inspections for cracking of the station (STA) 1241 
bulkhead fittings just above the canted pressure deck; a one-time 
determination of the edge margin at seven fastener positions on each 
side of the airplane; and related investigative/corrective actions if 
necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request to Revise ``Relevant Service Information'' Section

    Boeing asks that we revise the first sentence in the fourth 
paragraph of the ``Relevant Service Information'' section of the NPRM. 
That sentence now reads: ``For airplanes modified in accordance with 
Boeing Service Bulletin 747-53-2283 (AD 90-06-06). * * *'' Because 
Boeing Service Bulletin 747-53-2283 describes four different procedures 
and the modification referred to in the NPRM is a splice strap 
replacement, Boeing requests that the sentence read: ``For airplanes 
modified by replacing the splice strap in accordance with Boeing 
Service Bulletin 747-53-2283, Part III, Splice Strap Replacement and 
Boeing drawing 624U0006 * * *''
    We agree that the requested change clarifies the explanation in the 
``Relevant Service Information'' section in the preamble of the NPRM. 
However, since that section of the preamble does not reappear in the 
final rule, no change to the final rule is necessary.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    There are about 455 airplanes of the affected design in the 
worldwide fleet. This AD affects about 133 airplanes of U.S. registry. 
The actions take about 14 work hours per airplane, at an average labor 
rate of $80 per work hour. Based on these figures, the estimated cost 
of the AD for U.S. operators is $148,960, or $1,120 per airplane, per 
inspection cycle.

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 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.
    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.

[[Page 69591]]

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2007-25-17 Boeing: Amendment 39-15299. Docket No. FAA-2007-28620; 
Directorate Identifier 2007-NM-090-AD.

Effective Date

    (a) This AD becomes effective January 14, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series 
airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin 747-53A2658, dated February 22, 2007.

Unsafe Condition

    (d) This AD results from a report that an operator found a 1.65-
inch crack on the station (STA) 1241 bulkhead fitting on the left 
side of a Boeing Model 747-200F series airplane that had accumulated 
17,332 total flight cycles. We are issuing this AD to detect and 
correct cracking in the STA 1241 bulkhead fittings, which could 
result in reduced structural integrity of 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 and Corrective Action

    (f) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2658, dated 
February 22, 2007: Do internal surface high-frequency eddy current 
and external ultrasonic inspections for cracking of the STA 1241 
bulkhead fittings just above the canted pressure deck; determine the 
edge margin at seven fastener positions on each side of the 
airplane; and do all applicable related investigative/corrective 
actions; by doing all of the actions specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2658, dated 
February 22, 2007, except as provided by paragraphs (f)(1) and 
(f)(2) of this AD. Do all applicable related investigative/
corrective actions before further flight. Repeat the inspections 
thereafter at the applicable interval specified in paragraph 1.E., 
``Compliance'' of the service bulletin.
    (1) Where the service bulletin specifies to contact Boeing for 
appropriate action, before further flight, do the action using a 
method approved in accordance with the procedures specified in 
paragraph (g) of this AD.
    (2) Where the service bulletin specifies a compliance time after 
the date on the service bulletin, this AD requires compliance within 
the specified compliance time after the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (g)(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 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

    (h) You must use Boeing Alert Service Bulletin 747-53A2658, 
dated February 22, 2007, 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, 
Washington 98124-2207, for a copy of this service information. You 
may review copies 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/cfr/ibr-locations.html.


    Issued in Renton, Washington, on November 30, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. E7-23871 Filed 12-7-07; 8:45 am]

BILLING CODE 4910-13-P
