[Federal Register Volume 74, Number 173 (Wednesday, September 9, 2009)]
[Rules and Regulations]
[Pages 46331-46334]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-20838]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0476; Directorate Identifier 2008-NM-188-AD; 
Amendment 39-16006; AD 2009-18-10]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 707 Airplanes, and Model 
720 and 720B 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 707 airplanes, and Model 
720 and 720B series airplanes. The existing AD currently requires 
repetitive detailed inspections to detect cracks and corrosion on any 
existing repairs and at certain body stations (STA) of the visible 
surfaces of the wing to body terminal fittings including the web, 
flanges, and ribs; and applicable related investigative and corrective 
actions. This new AD retains the requirements of the existing AD and 
requires repetitive ultrasonic inspections to detect any stress 
corrosion cracks within the outboard flange of the left and right body 
terminal fittings at STA 820, and related investigative and corrective 
actions if necessary. This AD also provides an optional terminating 
action for the repetitive inspections. This AD also adds two airplanes 
to the applicability. This AD results from reports of cracks found in 
the wing to body terminal fittings during routine inspections. We are 
issuing this AD to detect and correct cracks and corrosion in the body 
terminal fittings above and below the floor, which could cause loss of 
support for the wing and could adversely affect the structural 
integrity of the airplane.

DATES: This AD becomes effective October 14, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of October 14, 
2009.

[[Page 46332]]


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: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6577; 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 2008-17-10, amendment 
39-15648 (73 FR 50703, August 28, 2008). The existing AD applies to 
certain Boeing Model 707 airplanes, and Model 720 and 720B series 
airplanes. That NPRM was published in the Federal Register on May 26, 
2009 (74 FR 24715). That NPRM proposed to continue to require detailed 
inspections and applicable related investigative and corrective 
actions. That NPRM also proposed to require repetitive ultrasonic 
inspections to detect any stress corrosion cracks within the outboard 
flange of the left and right body terminal fittings at station (STA) 
820, and related investigative and corrective actions if necessary. 
That NPRM also proposed an optional terminating action for the 
repetitive inspections. That NPRM also proposed to add two airplanes to 
the applicability.

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. The commenter concurs with the content of 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

    There are about 128 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
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                                                             Average  labor                           Number of U.S.- registered
               Action                      Work hours        rate  per hour     Cost per airplane             airplanes                 Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2008-17- 20....................             $80  $1,600 per inspection   11.........................  $17,600 per inspection
 10).                                                                         cycle.                                               cycle.
Inspections (new required action)..  20 to 30, depending on              80  $1,600 to $2,400 per    Up to 13...................  Up to $31,200 per
                                      group.                                  inspection cycle.                                    inspection cycle.
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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 39-15648 (73 FR 50703, August 28, 2008) and by 
adding the following new airworthiness directive (AD):


[[Page 46333]]


2009-18-10 Boeing: Amendment 39-16006. Docket No. FAA-2009-0476; 
Directorate Identifier 2008-NM-188-AD.

Effective Date

    (a) This AD becomes effective October 14, 2009.

Affected ADs

    (b) This AD supersedes AD 2008-17-10, amendment 39-15648.

Applicability

    (c) This AD applies to Boeing Model 707-100 long body, -200, -
100B long body, and -100B short body series airplanes; Model 707-
300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B 
series airplanes; certificated in any category; as identified in 
Boeing 707 Alert Service Bulletin A3524, Revision 1, dated September 
18, 2008.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

    (e) This AD results from new findings of cracks found in the 
wing to body terminal fittings during routine inspections. We are 
issuing this AD to detect and correct cracks and corrosion in the 
body terminal fittings above and below the floor, which could cause 
loss of support for the wing and could adversely affect the 
structural integrity 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 2008-17-10 With Updated Service 
Information

Inspections and Corrective Actions

    (g) For airplanes identified in Boeing 707 Special Attention 
Service Bulletin 3524, dated July 18, 2007: Within 24 months after 
October 2, 2008 (the effective date of AD 2008-17-10), do detailed 
inspections and applicable related investigative and corrective 
actions, by accomplishing all the actions specified in the 
Accomplishment Instructions of Boeing 707 Special Attention Service 
Bulletin 3524, dated July 18, 2007; or Boeing 707 Alert Service 
Bulletin A3524, Revision 1, dated September 18, 2008; except as 
provided by paragraph (h) of this AD. After the effective date of 
this AD, use only Boeing 707 Alert Service Bulletin A3524, Revision 
1, dated September 18, 2008. Repeat the detailed inspections 
thereafter at intervals not to exceed 24 months. Do all applicable 
related investigative and corrective actions before further flight.
    (h) If any crack or corrosion is found during any inspection 
required by paragraph (g) of this AD, and Boeing 707 Special 
Attention Service Bulletin 3524, dated July 18, 2007, or Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, 
specifies to contact Boeing for appropriate action: Before further 
flight, repair the terminal fittings using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.

No Information Submission

    (i) Although Boeing 707 Special Attention Service Bulletin 3524, 
dated July 18, 2007; and Boeing 707 Alert Service Bulletin A3524, 
Revision 1, dated September 18, 2008; specify to submit information 
to the manufacturer, this AD does not include that requirement.

New Requirements of This AD

Inspections

    (j) For Group 1 and Group 2 airplanes identified in Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, 
on which a modification or repair was done in accordance with Boeing 
707/720 Service Bulletin 2912, Revision 1, dated March 13, 1970: At 
the later of the times specified in paragraphs (j)(1) and (j)(2) of 
this AD, do an ultrasonic inspection to detect any stress corrosion 
cracks within the outboard flange of the left and right body 
terminal fittings at body station (STA) 820, and all applicable 
related investigative and corrective actions, by accomplishing all 
the actions specified in the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3524, Revision 1, dated September 18, 
2008, except as provided by paragraph (m) of this AD. Repeat the 
ultrasonic inspection thereafter at intervals not to exceed 24 
months or 2,000 flight cycles, whichever occurs first. Do all 
applicable related investigative and corrective actions before 
further flight.
    (1) Within 24 months or 2,000 flight cycles after the effective 
date of this AD, whichever occurs first.
    (2) Within 24 months or 2,000 flight cycles after doing the 
repair or modification, whichever occurs first.
    (k) For Group 3 and Group 4 airplanes identified in Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008: 
Within 2,000 flight cycles or 24 months after the effective date of 
this AD, whichever occurs first, do an ultrasonic inspection to 
detect any stress corrosion cracks within the outboard flange of the 
left and right body terminal fittings at STA 820, and all applicable 
corrective actions, by accomplishing all the actions specified in 
the Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3524, Revision 1, dated September 18, 2008, except as provided by 
paragraph (m) of this AD. Repeat the ultrasonic inspection 
thereafter at intervals not to exceed 24 months or 2,000 flight 
cycles, whichever occurs first. Do all applicable corrective actions 
before further flight.
    (l) For Group 4 airplanes identified in Boeing 707 Alert Service 
Bulletin A3524, Revision 1, dated September 18, 2008: Within 24 
months after the effective date of this AD, do detailed inspections 
for corrosion and cracking of the body terminal fittings at STA 820, 
and all applicable related investigative and corrective actions, by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3524, Revision 1, 
dated September 18, 2008, except as provided by paragraph (m) of 
this AD. Repeat the detailed inspections thereafter at intervals not 
to exceed 24 months. Do all applicable related investigative and 
corrective actions before further flight.

Exception to Certain Procedures

    (m) If any crack or corrosion is found during any inspection 
required by paragraph (j), (k), or (l) of this AD, and Boeing 707 
Alert Service Bulletin A3524, Revision 1, dated September 18, 2008, 
specifies to contact Boeing for appropriate action: Before further 
flight, repair the terminal fittings using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.

    Note 1:  Boeing 707 Alert Service Bulletin A3524, Revision 1, 
dated September 18, 2008, refers to Boeing 707/720 Service Bulletin 
2912, Revision 1, dated March 13, 1970, as an additional source of 
guidance for doing certain inspections and repairs.

Optional Terminating Action

    (n) Replacing a body terminal fitting with a fitting made from 
7075-T73 material, using a method approved in accordance with the 
procedures specified in paragraph (o) of this AD, terminates the 
repetitive inspections required by this AD for that fitting only.

Alternative Methods of Compliance (AMOCs)

    (o)(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: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6577; 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) 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

    (p) You must use Boeing 707 Alert Service Bulletin A3524, 
Revision 1, dated September 18, 2008, 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

[[Page 46334]]

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 
[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 August 18, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-20838 Filed 9-8-09; 8:45 am]
BILLING CODE 4910-13-P