
[Federal Register: February 26, 2009 (Volume 74, Number 37)]
[Rules and Regulations]               
[Page 8737-8739]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26fe09-14]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1006; Directorate Identifier 2008-NM-110-AD; 
Amendment 39-15822; AD 2009-04-16]
RIN 2120-AA64

 
Airworthiness Directives; Boeing Model 747-100, 747-100B, 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 superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 747-100, 747-100B, 747-
200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. 
That AD currently requires an inspection to determine if acceptable 
external skin doublers are installed at the stringer 6 (S-6) lap 
splices, between station (STA) 340 and STA 400. For airplanes without 
the acceptable external skin doublers, the existing AD also requires 
repetitive related investigative actions and corrective actions if 
necessary. The existing AD also provides an optional terminating 
modification for the repetitive related investigative actions. This new 
AD mandates the optional terminating modification. This AD results from 
a report of cracked fastener holes at the right S-6 lap splice between 
STA 340 and STA 380. We are issuing this AD to prevent cracking in the 
fuselage skin, which could result in rapid decompression and loss of 
structural integrity of the airplane.

DATES: This AD becomes effective April 2, 2009.
    On May 20, 2008 (73 FR 29042, May 20, 2008), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Alert Service Bulletin 747-53A2748, dated May 9, 2008.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207; telephone 206-544-9990; fax 206-766-5682; e-mail DDCS@boeing.com; 
Internet https://www.myboeingfleet.com.

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, Washington 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 supersedes AD 2008-10-15, amendment 
39-15522 (73 FR 29042, May 20, 2008). The existing AD applies to 
certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 
747-300, 747SR, and 747SP series airplanes. That NPRM was published in 
the Federal

[[Page 8738]]

Register on September 23, 2008 (73 FR 54755). That NPRM proposed to 
continue to require an inspection to determine if acceptable external 
skin doublers are installed at the stringer 6 (S-6) lap splices, 
between station (STA) 340 and STA 400. For airplanes without the 
acceptable external skin doublers, that NPRM also proposed to continue 
to require repetitive related investigative actions and corrective 
actions if necessary. That NPRM also proposed to require a previously 
optional terminating modification for the repetitive related 
investigative actions.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the single comment that has 
been received on the NPRM. The commenter, Boeing, concurs with the 
NPRM.

Conclusion

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

Costs of Compliance

    The inspection for acceptable external skin doublers that is 
required by AD 2008-10-15 and retained in this AD takes about 2 work 
hours per airplane, at an average labor rate of $80 per work hour. 
Based on these figures, the estimated cost of the inspection for U.S. 
operators is $27,840, or $160 per airplane.
    The cost for the terminating action depends on the results of the 
inspections. Therefore, we cannot calculate those costs because we do 
not know what doubler conditions operators will find.

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.

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 
removing amendment 39-15522 (73 FR 29042, May 20, 2008) and by adding 
the following new airworthiness directive (AD):

2009-04-16 Boeing: Amendment 39-15822. Docket No. FAA-2008-1006; 
Directorate Identifier 2008-NM-110-AD.

Effective Date

    (a) This AD becomes effective April 2, 2009.

Affected ADs

    (b) This AD supersedes AD 2008-10-15.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-200B, 
747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes, 
certificated in any category; as identified in Boeing Alert Service 
Bulletin 747-53A2748, dated May 9, 2008.

Unsafe Condition

    (d) This AD results from a report of cracked fastener holes at 
the right stringer 6 (S-6) lap splice between station (STA) 340 and 
STA 380. We are issuing this AD to prevent cracking in the fuselage 
skin, which could result in rapid decompression and loss of 
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.

Requirements of AD 2008-10-15

Service Bulletin Reference Paragraph

    (f) The term ``alert service bulletin,'' as used in this AD, 
means the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2748, dated May 9, 2008.

Inspection for Acceptable External Skin Doublers

    (g) For airplanes identified as Group 1, Configuration 2, in 
Boeing Alert Service Bulletin 747-53A2748, dated May 9, 2008: At the 
latest of the times specified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD, do an external general visual inspection to 
determine if acceptable external skin doublers are installed at the 
left- and right-side S-6 lap splices, in accordance with Part 1 of 
the alert service bulletin.
    (1) Prior to the accumulation of 10,000 total flight cycles.
    (2) Within 8,000 flight cycles after a modification was done in 
accordance with Boeing Service Bulletin 747-53-2253.
    (3) Within 15 days or 100 flight cycles after May 20, 2008 (the 
effective date of AD 2008-10-15), whichever occurs first.

Acceptable External Skin Doublers Found at Both Sides

    (h) If, during the inspection required by paragraph (g) of this 
AD, acceptable external skin doublers in accordance with the alert 
service bulletin are found installed at both the left- and right-
side S-6 lap splices, no further work is required by this AD.

Acceptable External Skin Doublers Not Found--Repetitive Related 
Investigative Actions and Corrective Actions

    (i) If, during the inspection required by paragraph (g) of this 
AD, acceptable external skin doublers in accordance with alert 
service bulletin are not found installed at either the left- or 
right-side S-6 lap splice: Before further flight, do all applicable 
related investigative and corrective actions by doing all actions 
specified in Part 2 of the alert service bulletin. Repeat the 
applicable related investigative actions thereafter at intervals not 
to exceed 300 flight cycles until the modification specified in 
paragraph (j) of this AD is done.

[[Page 8739]]

New Requirement of This AD

Terminating Modification

    (j) If, during the inspection required by paragraph (g) of this 
AD, acceptable external skin doublers as specified in the alert 
service bulletin are not found installed at either the left- or 
right-side S-6 lap splice: Within 3,000 flight cycles after doing 
the initial related investigative actions in paragraph (i) of this 
AD, or within 300 flight cycles after the effective date of this AD, 
whichever occurs later, install acceptable external skin doublers at 
both the left- and right-side S-6 lap splices, as applicable. The 
installation of the acceptable skin doublers is required on the side 
of the airplane that does not have the acceptable doublers already. 
The installation includes doing an open-hole high-frequency eddy 
current (HFEC) inspection of the skin for cracking, and trimming out 
cracking as applicable. Do all actions in accordance with the alert 
service bulletin. Doing this installation terminates the repetitive 
related investigative actions required by paragraph (i) of this AD.

    Note 1: The alert service bulletin refers to Boeing Service 
Bulletins 747-53-2253, Revision 3, dated March 24, 1994; and 747-53-
2272, Revision 18, dated May 16, 2002; as additional sources of 
service information for accomplishment of the modification 
(installation of acceptable external skin doublers).


    Note 2: AD 90-06-06, amendment 39-6490, requires, among other 
actions, a modification as specified in Boeing Service Bulletin 747-
53-2253, dated December 14, 1984.


    Note 3: AD 90-23-14, amendment 39-6801, requires inspections as 
specified in Boeing Service Bulletin 747-53-2253, Revision 2, dated 
March 29, 1990.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6437; fax (425) 917-6590; has the 
authority to approve AMOCs for this AD, if requested using 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

    (l) You must use Boeing Alert Service Bulletin 747-53A2748, 
dated May 9, 2008, to do the actions required by this AD, unless the 
AD specifies otherwise.
    (1) The Director of the Federal Register previously approved the 
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2748, dated May 9, 2008, on May 20, 2008 (73 FR 29042, May 20, 
2008).
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207; telephone 206-544-9990; fax 206-766-5682; e-mail 
DDCS@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information that is 
incorporated by reference 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 or 425-227-1152.
    (4) You may also review copies of the service information 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 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-3616 Filed 2-25-09; 8:45 am]

BILLING CODE 4910-13-P
