[Federal Register Volume 76, Number 228 (Monday, November 28, 2011)]
[Proposed Rules]
[Pages 72863-72866]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-30582]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1250; Directorate Identifier 2010-NM-031-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company 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. For certain airplanes, this proposed AD would require using 
redefined flight cycle counts, determining the type of material of the 
horizontal stabilizer, rear spar, upper chords, and lower chords on the 
inboard and outboard ends of the rear spar; repetitively inspecting for 
cracking of the horizontal stabilizer components; and repairing or 
replacing the chord, or modification of chord segments made from 7079 
aluminum, if necessary. For all airplanes, this proposed AD would 
require inspecting certain structurally significant items, and 
repairing discrepancies if necessary. This proposed AD was prompted by 
reports of stress corrosion cracking in the chord segments made from 
7079 aluminum in the horizontal stabilizer rear spar, and fatigue 
cracking in the chord segments made from 7075 aluminum. We are 
proposing this AD to detect and correct stress corrosion and/or fatigue 
cracking in the horizontal stabilizer, which could compromise the 
structural integrity of the stabilizer.

DATES: We must receive comments on this proposed AD by January 12, 
2012.

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 proposed 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; email 
[email protected]; 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.

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 
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 
(425) 917-6577; fax: (425) 917-6590, email: [email protected].

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-2011-1250; 
Directorate Identifier 2010-NM-031-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

    We have received numerous reports of stress corrosion cracking in 
the chord segments made from 7079 aluminum in the Model 707 horizontal 
stabilizer rear spar. 7079 aluminum is known to be susceptible to 
stress corrosion cracking. Development of stress corrosion cracking was 
slowed by the accomplishment of the actions specified in Boeing 707 
Service Bulletin 3356, Revision 2, dated December 12, 1991; and Boeing 
707 Service Bulletin 3381, Revision 2, dated January 31, 1991.
    In addition, we have received three reports of fatigue cracking in 
the upper chords of the horizontal stabilizer rear spar near the side 
of the body. These chords are made from 7075 aluminum. In all three 
cases, the actions specified in Boeing 707/720 Service Bulletin A3313, 
Revision 1, dated May 27, 1977, had been incorporated. The fatigue 
cracking in either 7075 or 7079 material configuration has occurred 
early in the life of the modified structure. The fatigue cracks were 
generated by frequent training flights that included multiple touch-
and-go cycles, which are most prevalent with military operators. These 
conditions, if not corrected, could result in stress corrosion and/or 
fatigue cracking in the horizontal stabilizer, which could compromise 
the structural integrity of the stabilizer.
    Parts made from 7079 aluminum have also been discovered on 
airplanes that were not originally delivered with those parts. 
Therefore, to adequately address the stress corrosion cracking in the 
chord segments in the rear spar of the horizontal stabilizer, it is 
necessary to determine the chord configuration on the airplane. 
Furthermore, it is also necessary to carefully maintain a record of 
that configuration until all chord segments of the rear spar of the 
horizontal stabilizers that are made from 7079 aluminum have been 
removed from the fleet. Since horizontal stabilizers can be swapped, it 
is also necessary to implement the inspections for early fatigue 
cracking on all airplanes, regardless of their current usage.

Relevant Service Information

    We have reviewed Boeing 707 Alert Service Bulletin A3515, dated 
December

[[Page 72864]]

19, 2007 (for Model 707 airplanes); and Boeing 707 Alert Service 
Bulletin A3516, dated April 4, 2008 (for Model 707 airplanes, and Model 
720 and 720B series airplanes).
    Boeing 707 Alert Service Bulletin A3515 describes procedures for 
the following actions:
     Counting flight-cycles to determine the compliance times.
     Determining the type of material of the horizontal 
stabilizer, rear spar, upper chords, and lower chords on the inboard 
and outboard ends of the rear spar.
     Repetitive special detailed inspections for cracking of 
the upper chord on the inboard end of the rear spar of the left and 
right side horizontal stabilizers.
     Repetitive high frequency eddy current inspections for 
cracking of the web flanges of the upper and lower chords of the rear 
spar of the left and right side horizontal stabilizers between 
stabilizer stations 92.55 and 272.55 for 7079 aluminum components.
     Repetitive low frequency eddy current inspections for 
cracking of the forward skin flanges of the upper and lower chords of 
the rear spar in the left and right side horizontal stabilizers from 
stabilizer stations -13.179 to 272.55 (for lower chords) and 92.55 to 
272.55 (for upper chords) for 7079 aluminum components.
     Repetitive special detailed inspections for cracking of 
the upper chord of the inboard side of the rear spar in the left and 
right side horizontal stabilizers from stabilizer station -13.179 to 
92.55 for 7079 aluminum components.
     Replacing certain chord components made from 7079 
aluminum.
     Corrective actions, including replacing the chord(s) with 
a new chord and contacting Boeing for repair instructions and doing the 
repair.
    Boeing 707 Alert Service Bulletin A3516 specifies one-time 
inspections of certain structurally significant items, and provides 
procedures for counting flight cycles for determining the compliance 
times for the inspections.

Related Rulemaking

    We issued AD 85-12-01, Amendment 39-5073 (50 FR 26690, June 28, 
1985), for Model 707 and 720 airplanes, as revised (AD 85-12-01 R1, 
Amendment 39-5439 (51 FR 36002, October 8, 1986). That AD requires 
structural inspections and repairs or replacement on certain high time 
airplanes that have exceeded their fatigue design life.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs. This proposed AD would require accomplishing the actions 
specified in the service information described previously, except as 
discussed below. The requirements of this proposed AD do not affect the 
requirements of AD 85-12-01 R1, Amendment 39-5439 (51 FR 36002, October 
8, 1986).

Differences Between the Proposed AD and Service Information

    Paragraph (i) of this proposed AD specifies determining the 
material of the structural components of the horizontal stabilizer in 
accordance with Boeing 707 Alert Service Bulletin A3515, dated December 
19, 2007. That service bulletin also specifies that this action be 
repeated. We have determined that accomplishing this action one time 
only will provide an adequate level of safety, provided that the 
component material is determined before further flight on any replaced 
horizontal stabilizer.
    Paragraph (i) of this proposed AD specifies a special detailed 
inspection of the upper chords, in accordance with Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007. That service bulletin 
specifies a compliance time of 180 days or 500 flight cycles (after the 
date on the service bulletin). This proposed AD, however, would remove 
the 500-flight-cycle compliance time to ensure that no airplane is 
unintentionally grounded, because it is possible an operator might 
exceed the flight-cycle grace period specified in paragraph (i) of this 
proposed AD before completing the inspection for chord material 
specified in paragraph (h) of this proposed AD. Similarly, paragraph 
(k) of this proposed AD removes the 250- and 1000-flight-cycle 
compliance times (specified in Boeing 707 Alert Service Bulletin A3515, 
dated December 19, 2007) for the initial inspection. This proposed AD 
would require these inspections within 180 days after the effective 
date of the AD.
    Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, 
specifies to contact the manufacturer for instructions on how to repair 
certain conditions, but this proposed AD would require repairing those 
conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD would affect 10 airplanes of U.S. 
registry. The following table provides the estimated costs for U.S. 
operators to comply with this proposed AD.

                                                                 Table--Estimated costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                   Number of U.S.-
              Action                      Work hours         Average labor       Parts         Cost per product      registered          Fleet cost
                                                             rate per hour                                            airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections.......................  24 to 32..............             $85              $0  $2,040 to $2,720 per               10  $20,400 to $27,200
                                                                                             inspection cycle.                      per inspection
                                                                                                                                    cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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

[[Page 72865]]

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 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 this 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),
    3. Will not affect intrastate aviation in Alaska, and
    4. 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

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 adding the following new AD:

The Boeing Company: Docket No. FAA-2011-1250; Directorate Identifier 
2010-NM-031-AD.

Comments Due Date

    (a) We must receive comments by January 12, 2012.

Affected ADs

    (b) This AD affects AD 85-12-01, Amendment 39-5073 (50 FR 26690, 
June 28, 1985), as revised by AD 85-12-01 R1, Amendment 39-5439, (51 
FR 36002, October 8, 1986).

Applicability

    (c) This AD applies to The Boeing Company 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 A3515, dated 
December 19, 2007, and Boeing 707 Alert Service Bulletin A3516, 
dated April 4, 2008.

Subject

    (d) Air Transport Association (ATA) of America Code 55: 
Stabilizers.

Unsafe Condition

    (e) This AD was prompted by reports of stress corrosion cracking 
in the chord segments made from 7079 aluminum in the horizontal 
stabilizer rear spar, and fatigue cracking in the chord segments 
made from 7075 aluminum. The Federal Aviation Administration is 
issuing this AD to detect and correct stress corrosion and/or 
fatigue cracking in the horizontal stabilizer, which could 
compromise the structural integrity of the stabilizer.

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.

Flight Cycle Counting Procedure

    (g) Flight cycles, as used in this AD, must be counted as 
defined in Boeing 707 Alert Service Bulletin A3515, dated December 
19, 2007 (for Model 707 airplanes); or Boeing 707 Alert Service 
Bulletin A3516, dated April 4, 2008 (for Model 707 airplanes, and 
Model 720 and 720B series airplanes).

Determine Material of the Components of the Horizontal Stabilizer

    (h) For airplanes identified in Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007: At the earlier of the times 
specified in paragraphs (h)(1) and (h)(2) of this AD, determine the 
type of material of the horizontal stabilizer, rear spar, upper 
chords, and lower chords on the inboard and outboard ends of the 
rear spar, in accordance with Part 2 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007.
    (1) Within 180 days after the effective date of this AD.
    (2) Before further flight after any horizontal stabilizer is 
replaced after the effective date of this AD.

Repetitive Inspections of 7075 Aluminum Components

    (i) For airplanes with horizontal stabilizer components made 
from 7075 aluminum, as determined during the inspection required by 
paragraph (h) of this AD: Within 180 days after the effective date 
of this AD, and before further flight after any replacement of the 
horizontal stabilizer, do a special detailed inspection for cracking 
of the upper chord on the inboard end of the rear spar in the left 
and right side horizontal stabilizers, from stabilizer station -
13.179 to 92.55, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007. Repeat the inspections thereafter at intervals 
not to exceed 500 flight cycles, and before further flight after any 
replacement of the horizontal stabilizer, except as provided by 
paragraph (j) of this AD. If any cracking is found, before further 
flight, either repair the cracking in accordance with Part 3 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, except as required by paragraph (n) 
of this AD; or replace the chord with a new chord, in accordance 
with Part 6 of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007.

    Note 1: For the purposes of this AD, a special detailed 
inspection is ``an intensive examination of a specific item, 
installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and/or equipment. Intricate 
cleaning and substantial access or disassembly procedure may be 
required.

    (j) For airplanes on which the chord is replaced with a new 
chord in accordance with Part 6 of the Accomplishment Instructions 
of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007: 
Within 4,000 flight cycles after the chord replacement, do the 
inspections required by paragraph (i) of this AD, and repeat the 
inspections thereafter at the times specified in paragraph (i) of 
this AD.

Repetitive Inspections of 7079 Aluminum Components

    (k) For airplanes with horizontal stabilizers that have 
components of the chords of the rear spar made from 7079 aluminum, 
as determined during the inspection required by paragraph (h) of 
this AD: Within 180 days after the effective date of this AD, do the 
actions required by paragraphs (k)(1), (k)(2), and (k)(3) of this 
AD, and repeat those actions at the applicable intervals specified 
in paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
    (1) Do a special detailed inspection for cracking of the upper 
chord of the inboard side of the rear spar in the left and right 
side horizontal stabilizers from stabilizer station -13.179 to 
92.55, in accordance with Part 3 of the Accomplishment Instructions 
of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. 
Repeat the inspection thereafter at intervals not to exceed 250 
flight cycles or 180 days, whichever occurs first. If any cracking 
is found during any inspection required by this paragraph, before 
further flight, either repair the cracking, in accordance with Part 
3 of the Accomplishment Instructions of Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007, except as required by 
paragraph (n) of this AD; or replace the chord with a new chord, in 
accordance with Part

[[Page 72866]]

6 of Boeing 707 Alert Service Bulletin A3515, dated December 19, 
2007.
    (2) Do a high frequency eddy current inspection for cracking of 
the web flanges of the upper and lower chords of the rear spar in 
the left and right side horizontal stabilizers from stabilizer 
stations 92.55 to 272.55, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007. Repeat the inspection thereafter at 
intervals not to exceed 1,000 flight cycles or 180 days, whichever 
occurs first. If any cracking is found during any inspection 
required by this paragraph, before further flight, do the actions 
specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD.
    (i) Determine whether the cracking meets the limits specified in 
Part 4 of the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007, and whether a 
previous repair has been done; determine if all 7079 upper and lower 
chord segments installed on the horizontal stabilizer have had the 
Part II, Group 1, Preventative Modification specified in Boeing 707 
Service Bulletin 3356 done; and do all applicable repairs and 
modifications, in accordance with Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007. Do the actions required by this 
paragraph in accordance with Part 4 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007, except as required by paragraph (n) of this AD. 
Do all applicable repairs and modifications before further flight.
    (ii) Replace the chord with a new chord, in accordance with Part 
6 of Boeing 707 Alert Service Bulletin A3515, dated December 19, 
2007.
    (3) Do low frequency eddy current (LFEC) inspections for 
cracking of the forward skin flanges of the upper and lower chords 
of the rear spar in the left and right side horizontal stabilizers 
from stabilizer stations -13.179 to 272.55 (for lower chords) and 
92.55 to 272.55 (for upper chords), in accordance with Part 5 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007. Repeat the inspections thereafter at 
intervals not to exceed 1,000 flight cycles or 180 days, whichever 
occurs first. If any cracking is found during any inspection 
required by this paragraph, before further flight, do the actions 
specified in either paragraph (k)(3)(i) or paragraph (k)(3)(ii) of 
this AD.
    (i) Repair cracking, and determine whether all 7079 upper and 
lower chord segments installed on the horizontal stabilizer have had 
the Part II--Preventative Modification specified in Boeing 707 
Service Bulletin 3381 done, and do all applicable modifications, in 
accordance with Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007. Do the actions required by this paragraph in 
accordance with Part 5 of the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, except as 
required by paragraph (n) of this AD. Do all applicable 
modifications before further flight.
    (ii) Replace the chord with a new chord, in accordance with Part 
6 of Boeing 707 Alert Service Bulletin A3515, dated December 19, 
2007.

Modification/Chord Replacement

    (l) For airplanes identified in Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007, with horizontal stabilizers 
that have rear spar chord components made from 7079 aluminum and 
have not had embodied the modification of Part II of Boeing 707 
Service Bulletin 3381, dated July 25, 1980; or Revision 1, dated 
July 31, 1981: Before further flight after determining the type of 
material in accordance with paragraph (h) of this AD, modify all 
7079 chord segments still installed on the horizontal stabilizer, in 
accordance with Part 5 of the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007; or 
replace the chord, in accordance with Part 6 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007.

Supplemental Structural Inspection Document Inspections

    (m) For all airplanes: Within 180 days or 1,000 flight cycles 
after the effective date of this AD, whichever occurs first, do the 
inspections of the applicable structurally significant items 
specified in and in accordance with the Accomplishment Instructions 
of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. If 
any cracking is found, before further flight, repair in accordance 
with the procedures specified in paragraph (q) of this AD. The 
inspections required by AD 85-12-01 R1, Amendment 39-5439 (51 FR 
36002, October 8, 1986), are still required, except, as of the 
effective date of this AD, the flight-cycle interval for the 
repetitive inspections specified in paragraph 1.E., ``Compliance,'' 
of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008, 
must be counted in accordance with the requirements of paragraph (g) 
of this AD.

Exceptions to the Service Information

    (n) If any cracking is found during any inspection required by 
this AD, and Boeing 707 Alert Service Bulletin A3515, dated December 
19, 2007, specifies to contact Boeing for appropriate action: Before 
further flight, repair the cracking using a method approved in 
accordance with the procedures specified in paragraph (q) of this 
AD.
    (o) Where Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007, specifies that operators ``refer to'' NDT 
procedures, the procedures must be done in accordance with the 
service information identified in paragraphs (o)(1), (o)(2), and 
(o)(3) of this AD, as applicable.
    (1) Subject 51-00-00, ``Structures-General,'' Figure 20, 
``Electrical Conductivity Measurement for Aluminum,'' of Part 6-Eddy 
Current, of the Boeing 707/720 Nondestructive Test Manual, Document 
D6-48023, Revision 118, dated July 15, 2011.
    (2) Subject 55-10-07, ``Horizontal Stabilizer,'' of Part 6-Eddy 
Current, of the Boeing 707/720 Nondestructive Test Manual, Document 
D6-48023, Revision 118, dated July 15, 2011.
    (3) Subject 51-01-00, ``Orientation and Preparation for 
Testing'' of Part 1-General, of the Boeing 707/720 Nondestructive 
Test Manual, Document D6-48023, Revision 118, dated July 15, 2011.

Parts Installation

    (p) As of the effective date of this AD, no person may install 
any horizontal stabilizer assembly with any chord segment having a 
part number other than that identified in paragraph 2.C.2. of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, on any 
airplane.

Alternative Methods of Compliance (AMOCs)

    (q)(1) The Manager, Seattle Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the ACO, send it to the attention of the 
person identified in the Related Information section of this AD 
Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that 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.

Related Information

    (r) For more information about this AD, contact Berhane Alazar, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: (425) 917-6577; fax: (425) 917-6590; email: 
[email protected].
    (s) 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; email 
[email protected]; 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.

    Issued in Renton, Washington, on November 10, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-30582 Filed 11-25-11; 8:45 am]
BILLING CODE 4910-13-P