
[Federal Register Volume 74, Number 99 (Tuesday, May 26, 2009)]
[Proposed Rules]
[Pages 24715-24718]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-12112]


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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]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that 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 proposed AD would retain the requirements of the existing 
AD and would require 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 proposed AD would also provide 
for an optional terminating action for the repetitive inspections. This 
proposed AD also adds two airplanes to the applicability. This proposed 
AD results from reports of cracks found in the wing to body terminal 
fittings during routine inspections. We are proposing 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: We must receive comments on this proposed AD by July 10, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    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,

[[Page 24716]]

me.boecom@boeing.com; Internet, https://www.myboeingfleet.com. You may 
review copies of the referenced 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.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0476; 
Directorate Identifier 2008-NM-188-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On August 6, 2008, we issued AD 2008-17-10, amendment 39-15648 (73 
FR 50703, August 28, 2008), for certain Boeing Model 707 airplanes, and 
Model 720 and 720B series airplanes. That AD 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. That AD 
resulted from reports of cracks found in the wing to body terminal 
fittings during routine inspections. We issued that AD to detect and 
correct cracks and corrosion in the body terminal fittings, which could 
cause loss of support for the wing and could adversely affect the 
structural integrity of the airplane.

Relevant Service Information

    We have reviewed Boeing 707 Alert Service Bulletin A3524, Revision 
1, dated September 18, 2008. (AD 2008-17-10 refers to Boeing 707 
Special Attention Service Bulletin 3524, dated July 18, 2007, as the 
appropriate source of service information for accomplishing the 
required actions in that AD.) Revision 1 of this service bulletin adds 
procedures, for certain airplanes, to do repetitive ultrasonic 
inspections for stress corrosion cracks within the outboard flange of 
the left and right body terminal fittings at STA 820, and if necessary, 
related investigative and corrective actions. The related investigative 
action is an inspection to determine whether the modification or repair 
meets the specifications of Boeing 707/720 Service Bulletin 2912, 
Revision 1, dated March 13, 1970. The corrective action is contacting 
Boeing for repair instructions. Revision 1 of Boeing 707 Alert Service 
Bulletin A3524 also adds two airplanes to the effectivity.
    Boeing 707 Alert Service Bulletin A3524, Revision 1, refers to 
Boeing 707/720 Service Bulletin 2912, Revision 1, dated March 13, 1970, 
as an additional source of service information for doing certain 
inspections and repairs.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2008-17-10 and would retain the requirements of the 
existing AD. This proposed AD would also add, for certain airplanes, 
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 proposed AD would also add two airplanes to the 
applicability.

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 proposed AD.

                                                 Estimated Costs
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                                                   Average                      Number of U.S.-
            Action                Work hours      labor rate      Cost per        registered        Fleet cost
                                                   per hour       airplane         airplanes
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Inspections (required by AD    20..............          $80  $1,600 per       11..............  $17,600 per
 2008-17-10).                                                  inspection                         inspection
                                                               cycle.                             cycle.
Inspections (new proposed      20 to 30,                  80  $1,600 to        Up to 13........  Up to $31,200
 action).                       depending on                   $2,400 per                         per inspection
                                group.                         inspection                         cycle.
                                                               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

[[Page 24717]]

products identified in this rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by removing amendment 39-15648 (73 FR 
50703, August 28, 2008) and adding the following new AD:

Boeing: Docket No. FAA-2009-0476; Directorate Identifier 2008-NM-
188-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 10, 
2009.

Affected ADs

    (b) This AD supersedes AD 2008-17-10.

Applicability

    (c) This AD applies to 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

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 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,

[[Page 24718]]

2008, refers to Boeing 707/720 Service Bulletin 2912, Revision 1, 
dated March 13, 1970, as an additional source of service information 
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 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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.

    Issued in Renton, Washington, on May 15, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-12112 Filed 5-22-09; 8:45 am]
BILLING CODE 4910-13-P


