Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400, 747SR, and 747SP Series Airplanes

[Federal Register Volume 74, Number 236 (Thursday, December 10, 2009)]
[Rules and Regulations]
[Pages 65403-65406]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-29222]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0682; Directorate Identifier 2008-NM-200-AD; 
Amendment 39-16131; AD 2009-25-11]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747-400, 747SR, and 747SP Series Airplanes

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

ACTION: Final rule.

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[[Page 65404]]

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 747 airplanes. The existing 
AD currently requires repetitive inspections for cracking, and repair 
as necessary, of lower lobe body frames (sections 42 and 46) of the 
fuselage. The existing AD also provides for optional modification of 
the frames, which terminates the repetitive inspections. This new AD 
requires additional repetitive inspections for cracking of certain 
fuselage frames, and corrective actions if necessary. This AD results 
from a new report of a crack found in a body frame with a tapered side 
guide bracket at fuselage station 1800, located on the left side 
between stringers 39 and 40; the frame was severed. We are issuing this 
AD to detect and correct the loss of structural integrity of the 
fuselage, which could result in rapid depressurization of the airplane.

DATES: This AD becomes effective January 14, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of January 14, 
2010.

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 [email protected]; 
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 86-18-01, amendment 39-
5390 (51 FR 28691, August 11, 1986). The existing AD applies to certain 
Boeing Model 747 airplanes. That NPRM was published in the Federal 
Register on August 5, 2009 (74 FR 38995). That NPRM proposed to 
continue to require repetitive inspections for cracking, and repair as 
necessary, of lower lobe body frames (sections 42 and 46) of the 
fuselage. That NPRM also provides for optional modification of the 
frames, which terminates the repetitive inspections. That NPRM also 
proposed to require additional repetitive inspections for cracking of 
certain fuselage frames, and corrective actions if necessary.

Comments

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

Explanation of Change to Final Rule

    AD 86-18-01 does not provide a compliance time for doing the 
corrective actions required by paragraphs (g) and (h) of this AD. 
However, we have determined that it is implicit in the existing AD that 
the corrective actions be done before further flight. Sections 91.7 and 
121.153 of the Federal Aviation Regulations (14 CFR 91.7 and 14 CFR 
121.153) already require that aircraft be in an airworthy condition 
before they can be operated. We have changed paragraphs (g) and (h) of 
this AD to include those compliance times.

Conclusion

    We reviewed the relevant data, including the comment that has been 
received, and determined that air safety and the public interest 
require adopting the AD with the change described previously. We also 
determined that this change will not increase the economic burden on 
any operator or increase the scope of the AD.

Costs of Compliance

    There are about 237 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of
                                                 Average                            U.S.-
             Action                Work hours   labor rate   Cost per airplane    registered      Fleet cost
                                                 per hour                         airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 86-           370          $80  $29,600, per                 112  $3,315,200, per
 18-01).                                                     inspection cycle.                 inspection cycle.
Additional inspections (new                 6           80  $480, per                     87  $41,760, per
 action).                                                    inspection cycle.                 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

[[Page 65405]]

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 39-5390 (51 FR 28691, August 11, 1986) and by adding 
the following new airworthiness directive (AD):

2009-25-11 Boeing: Amendment 39-16131. Docket No. FAA-2009-0682; 
Directorate Identifier 2008-NM-200-AD.

Effective Date

    (a) This AD becomes effective January 14, 2010.

Affected ADs

    (b) This AD supersedes AD 86-18-01, Amendment 39-5390.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-300, 747-400, 747SR, and 747SP series airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin 747-53A2749, dated September 25, 2008.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from a report of a crack found in a body 
frame with a tapered side guide bracket at fuselage station 1800, 
located on the left side between stringers 39 and 40; the frame was 
severed. The Federal Aviation Administration is issuing this AD to 
detect and correct the loss of structural integrity of the fuselage, 
which could result in rapid depressurization of 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.

Restatement of Requirements of AD 86-18-01, With Revised Service 
Information

Repetitive Inspections

    (g) For airplanes listed in Boeing Alert Service Bulletin 747-
53A2237, Revision 1, dated March 28, 1986: Perform a detailed visual 
inspection for frame cracking from fuselage section 540 to 760, and 
1820 to 1900, stringers 35 left to 42 left, in accordance with 
Section III of Boeing Alert Service Bulletin 747-53A2237, Revision 
1, dated March 28, 1986. Do the inspection at the time specified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. If 
any crack is found, before further flight, repair in accordance with 
a method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA, or using a method approved in accordance with the 
procedures specified in paragraph (p) of this AD. Repeat the 
inspection at intervals not to exceed 3,000 landings until the 
terminating action specified in paragraph (g)(4) or (k) of this AD 
is performed.
    (1) Within 300 landings for airplanes that have accumulated more 
than 12,000 landings on September 17, 1986 (the effective date of AD 
86-18-01, amendment 39-5390).
    (2) Within 800 landings for airplanes that have accumulated 
10,000 to 12,000 landings on September 17, 1986.
    (3) Within 800 landings or prior to the accumulation of 10,000 
landings, whichever occurs later, for airplanes that have 
accumulated less than 10,000 landings on September 17, 1986.
    (4) Modification of the frames before the effective date of this 
AD in accordance with Boeing Alert Service Bulletin 747-53A2237, 
Revision 1, dated March 28, 1986, constitutes terminating action for 
the repetitive inspections required by paragraph (g) of this AD.
    (h) For airplanes listed in Boeing Alert Service Bulletin 747-
53A2259, Revision 1, dated April 18, 1986: Perform a visual 
inspection of cargo side guide support brackets from fuselage 
station 1500 to 1800, right and left hand side, for a proper 
machined taper in accordance with Section III of Boeing Alert 
Service Bulletin 747-53A2259, Revision 1, dated April 18, 1986. Do 
the inspection at the time specified in paragraph (h)(1), (h)(2), or 
(h)(3) of this AD, as applicable. If any cargo side guide support 
bracket is improperly tapered, before further flight, perform a 
detailed visual inspection of the frame area adjacent to the 
untapered bracket for cracking in accordance with Boeing Alert 
Service Bulletin 747-53A2259, Revision 1, dated April 18, 1986. If 
any crack is found, before further flight, repair in accordance with 
a method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA, or using a method approved in accordance with the 
procedures specified in paragraph (p) of this AD. Repeat the 
detailed visual inspection at intervals not to exceed 3,000 landings 
until the terminating action specified in paragraph (h)(4) of this 
AD is performed. Accomplishment of the inspections required by 
paragraph (k) of this AD terminates the inspections required by this 
paragraph.
    (1) Within 300 landings for airplanes that have accumulated more 
than 12,000 landings on September 17, 1986 (the effective date of AD 
86-18-01, amendment 39-5390).
    (2) Within 800 landings for airplanes that have accumulated 
10,000 to 12,000 landings on September 17, 1986.
    (3) Within 800 landings or prior to the accumulation of 10,000 
landings, whichever occurs later, for airplanes that have 
accumulated less than 10,000 landings on September 17, 1986.
    (4) Installation of a tapered strap adjacent to the affected 
brackets before the effective date of this AD in accordance with 
Boeing Alert Service Bulletin 747-53A2259, Revision 1, dated April 
18, 1986, constitutes terminating action for the repetitive 
inspections required by paragraph (h) of this AD.
    (i) For Boeing Model 747SR airplanes only, based on continued 
mixed operation of cabin pressure differentials, the initial 
inspection thresholds and reinspection intervals specified in AD 86-
18-01 may be multiplied by a 1.2 adjustment factor. This provision 
is not applicable to paragraphs (k), (m), and (n) of this AD.
    (j) For the purposes of complying with AD 86-18-01, the number 
of landings may be determined to equal the number of pressurization 
cycles where the cabin pressure differential was greater than 2.0 
pounds per square inch. This provision is not applicable to 
paragraphs (k), (m), and (n) of this AD.

New Requirements of This AD

Repetitive Inspections

    (k) For airplanes identified in Boeing Alert Service Bulletin 
747-53A2749, dated September 25, 2008, that have accumulated 22,000 
or fewer total flight cycles as of the effective date of this AD: Do 
initial and repetitive detailed inspections for frame cracking from 
fuselage body stations 1500 to 1800, stringers 39 to 40, by doing 
all the actions specified in the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2749, dated September 25, 2008, 
except as required by paragraph (l) of this AD. Do the inspections 
and corrective actions at the times specified in paragraph 1.E. of 
Boeing Alert Service Bulletin 747-53A2749, dated September 25, 2008, 
except as required by paragraphs (m) and (n) of this AD. 
Accomplishment of the inspections required by this paragraph 
terminates the inspections required by paragraph (h) of this AD.

Exceptions to Service Bulletin Procedures

    (l) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2749, dated

[[Page 65406]]

September 25, 2008, specifies to contact Boeing for appropriate 
action: Before further flight, repair the crack using a method 
approved in accordance with the procedures specified in paragraph 
(p) of this AD.
    (m) Where Boeing Alert Service Bulletin 747-53A2749, dated 
September 25, 2008, specifies a compliance time after the date of 
the service bulletin, this AD requires compliance within the 
specified compliance time after the effective date of this AD.
    (n) Where Boeing Alert Service Bulletin 747-53A2749, dated 
September 25, 2008, specifies a compliance time related to 
accomplishing an action ``as given in Boeing Service Bulletin 747-
53A2259,'' this AD requires compliance within the specified 
compliance time after the applicable compliance time required by 
paragraph (h) of this AD.

Terminating Action

    (o) Accomplishing the repetitive frame inspections required by 
AD 2006-05-02, amendment 39-14499; or AD 2005-20-30, amendment 39-
14327; terminates the inspections required by paragraphs (g), (h), 
and (k) of this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle Aircraft Certification Office (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: 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; or, e-mail information to [email protected].
    (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) AMOCs approved previously in accordance with paragraph (A) 
of AD 86-18-01, are approved as alternative methods of compliance 
with the corresponding requirements of paragraph (g) of this AD.
    (4) AMOCs approved previously in accordance with paragraph (B) 
of AD 86-18-01, are approved as alternative methods of compliance 
with the corresponding requirements of paragraph (h) of this AD.
    (5) 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

    (q) You must use the service information contained in Table 1 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.

                                   Table 1--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                 Document                            Revision                              Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 747-53A2237  1...........................  March 28, 1986.
Boeing Alert Service Bulletin 747-53A2259  1...........................  April 18, 1986.
Boeing Alert Service Bulletin 747-53A2749  Original....................  September 25, 2008.
----------------------------------------------------------------------------------------------------------------

Boeing Alert Service Bulletin 747-53A2259, Revision 1, dated April 
18, 1986, contains the following effective pages:

----------------------------------------------------------------------------------------------------------------
                Page Nos.                  Revision level shown on page             Date shown on page
----------------------------------------------------------------------------------------------------------------
2, 3, 5, 6, 9-11, 15, 16, 18-24..........  Original....................  March 28, 1986.
1, 4, 7, 8, 12-14, 17, 25, 26............  Revision 1..................  April 18, 1986.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the 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 
[email protected]; Internet https://www.myboeingfleet.com.
    (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 or 425-227-1152.
    (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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 1, 2009.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-29222 Filed 12-9-09; 8:45 am]
BILLING CODE 4910-13-P

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